U.S. patent application number 17/556743 was filed with the patent office on 2022-09-08 for system and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system.
The applicant listed for this patent is ExxonMobil Upstream Research Company, General Electric Company. Invention is credited to Sulabh K. Dhanuka, Richard A. Huntington, Ilya Aleksandrovich Slobodyanskiy.
Application Number | 20220282668 17/556743 |
Document ID | / |
Family ID | 1000006362064 |
Filed Date | 2022-09-08 |
United States Patent
Application |
20220282668 |
Kind Code |
A1 |
Huntington; Richard A. ; et
al. |
September 8, 2022 |
SYSTEM AND METHOD FOR LOAD CONTROL WITH DIFFUSION COMBUSTION IN A
STOICHIOMETRIC EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEM
Abstract
A system is provided with a turbine combustor having a first
diffusion fuel nozzle, wherein the first diffusion fuel nozzle is
configured to produce a diffusion flame. The system includes a
turbine driven by combustion products from the diffusion flame in
the turbine combustor. The system also includes an exhaust gas
compressor, wherein the exhaust gas compressor is configured to
compress and route an exhaust gas from the turbine to the turbine
combustor along an exhaust recirculation path. In addition, the
system includes a control system configured to control flow rates
of at least one oxidant and at least one fuel to the turbine
combustor in a stoichiometric control mode and a non-stoichiometric
control mode, wherein the stoichiometric control mode is configured
to change the flow rates and provide a substantially stoichiometric
ratio of the at least one fuel with the at least one oxidant, and
the non-stoichiometric control mode is configured to change the
flow rates and provide a non-stoichiometric ratio of the at least
one fuel with the at least one oxidant.
Inventors: |
Huntington; Richard A.;
(Houston, TX) ; Dhanuka; Sulabh K.; (Houston,
TX) ; Slobodyanskiy; Ilya Aleksandrovich;
(Greenville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company
ExxonMobil Upstream Research Company |
Schenectady
Spring |
NY
TX |
US
US |
|
|
Family ID: |
1000006362064 |
Appl. No.: |
17/556743 |
Filed: |
December 20, 2021 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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16284746 |
Feb 25, 2019 |
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17556743 |
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14067563 |
Oct 30, 2013 |
10215412 |
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16284746 |
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61722118 |
Nov 2, 2012 |
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61722115 |
Nov 2, 2012 |
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61722114 |
Nov 2, 2012 |
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61722111 |
Nov 2, 2012 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23J 2219/10 20130101;
F02C 6/18 20130101; F23R 3/346 20130101; F23J 2215/40 20130101;
F23J 2215/10 20130101; F23J 15/006 20130101; Y02E 20/32 20130101;
F02C 9/34 20130101; F02C 1/06 20130101; Y02T 50/60 20130101; F23J
2215/50 20130101; F23R 3/28 20130101; F23N 1/022 20130101; F02C
3/30 20130101; F23N 5/006 20130101; F23J 15/02 20130101; F23R 3/26
20130101; F02C 9/28 20130101; F23C 9/00 20130101; F05D 2270/08
20130101; F05D 2270/0831 20130101; Y02E 20/16 20130101; F02C 7/228
20130101; F02C 3/22 20130101; F23R 3/34 20130101; F02C 3/34
20130101; F01K 23/10 20130101 |
International
Class: |
F02C 3/34 20060101
F02C003/34; F02C 3/30 20060101 F02C003/30; F23R 3/34 20060101
F23R003/34; F02C 7/228 20060101 F02C007/228; F02C 9/34 20060101
F02C009/34; F23R 3/28 20060101 F23R003/28 |
Claims
1. A system, comprising: a turbine combustor, comprising: a
chamber; and a diffusion nozzle comprising a first passage
configured to inject a first flow of a fuel into the chamber, a
second passage configured to inject a second flow of an oxidant
into the chamber, and a third passage configured to inject a third
flow of a diluent into the chamber, wherein the first passage, the
second passage, and the third passage are fluidly isolated from
each other along the diffusion nozzle; a turbine configured to be
driven by combustion products generated from a diffusion flame
produced by the turbine combustor, wherein the turbine is
configured to output an exhaust gas; an exhaust gas compressor
configured to compress the exhaust gas and route the exhaust gas
from the turbine, along an exhaust recirculation path, and to the
turbine combustor such that the exhaust gas forms at least a
portion of the third flow of the diluent; and a control system
configured to control a first flow rate of the first flow, a second
flow rate of the second flow, a third flow rate of the third flow,
or any combination thereof based on a load of the system.
2. The system of claim 1, wherein the control system is configured
to reduce the first flow rate of the first flow, the second flow
rate of the second flow, the third flow rate of the third flow, or
any combination thereof based on the load of the system changing
from a first load to a second load.
3. The system of claim 1, wherein the control system is configured
to increase the first flow rate of the first flow, the second flow
rate of the second flow, the third flow rate of the third flow, or
any combination thereof based on the load of the system changing
from a first load to a second load.
4. The system of claim 1, wherein the control system is configured
to control the first flow rate of the first flow, the second flow
rate of the second flow, the third flow rate of the third flow, or
any combination thereof based on the load of the system and such
that a stoichiometric ratio is maintained while the load
corresponds to a full load and while the load corresponds to a
partial load, wherein the stoichiometric ratio corresponds to an
equivalence ratio between 0.95 and 1.05.
5. The system of claim 1, wherein the second passage is configured
to inject the second flow of a mixture of the oxidant and an
additional diluent into the chamber.
6. The system of claim 1, wherein the diffusion nozzle comprises a
fourth passage configured to inject a fourth flow of an additional
fuel, an additional oxidant, or an additional diluent into the
chamber, wherein the fourth passage is fluidly isolated from the
first passage, the second passage, and the third passage along the
diffusion nozzle.
7. The system of claim 1, comprising an additional diffusion nozzle
comprising a fourth passage configured to inject a fourth flow of
an additional fuel into the chamber, a fifth passage configured to
inject a fifth flow of an additional oxidant into the chamber, and
a sixth passage configured to inject a sixth flow of an additional
diluent into the chamber, wherein the fourth passage, the fifth
passage, and the sixth passage are fluidly isolated from each other
along the additional diffusion nozzle.
8. The system of claim 7, wherein the control system is configured
to control a fourth flow rate of the fourth flow, a fifth flow rate
of the fifth flow, a sixth flow rate of the sixth flow, or any
combination thereof based on the load of the system.
9. The system of claim 7, wherein the control system is configured
to control the diffusion nozzle and the additional diffusion nozzle
such that a stoichiometric ratio is maintained while the load
corresponds to a full load and while the load corresponds to a
partial load, wherein the stoichiometric ratio corresponds to an
equivalence ratio between 0.95 and 1.05.
10. The system of claim 1, comprising at least one valve or pump,
wherein the control system is configured to control the first flow
rate of the first flow, the second flow rate of the second flow,
the third flow rate of the third flow, or any combination thereof
based on the load of the system by controlling the at least one
valve or pump.
11. A system, comprising: a turbine combustor, comprising: a
chamber; and a diffusion nozzle comprising a first passage
configured to inject a fuel into the chamber, a second passage
configured to inject an oxidant into the chamber, and a third
passage configured to inject a diluent into the chamber, wherein
the first passage, the second passage, and the third passage are
fluidly isolated from each other along the diffusion nozzle; a
turbine configured to be driven by combustion products generated
from a diffusion flame produced by the turbine combustor, wherein
the turbine is configured to output an exhaust gas; an exhaust gas
compressor configured to compress the exhaust gas and route the
exhaust gas from the turbine, along an exhaust recirculation path,
and to the turbine combustor such that the exhaust gas forms at
least a portion of the diluent; and a control system configured to
control the system such that: the fuel is moved through the first
passage at a first flow rate based on the system being operated at
a full load, and the fuel is moved through the first passage at a
second flow rate based on the system being operated at a partial
load, wherein the second flow rate differs from the first flow
rate; or the oxidant is moved through the second passage at a third
flow rate based on the system being operated at the full load, and
the oxidant is moved through the second passage at a fourth flow
rate based on the system being operated at the partial load,
wherein the fourth flow rate differs from the third flow rate; or
the diluent is moved through the third passage at a fifth flow rate
based on the system being operated at the full load, and the
diluent is moved through the third passage at a sixth flow rate
based on the system being operated at the partial load, wherein the
sixth flow rate differs from the fifth flow rate; or any
combination thereof.
12. The system of claim 11, wherein the control system is
configured to maintain a stoichiometric ratio while the system is
being operated at the full load and while the system is being
operated at the partial load, wherein the stoichiometric ratio
corresponds to an equivalence ratio between 0.95 and 1.05.
13. The system of claim 11, comprising an additional diffusion
nozzle comprising a fourth passage configured to inject an
additional fuel into the chamber, a fifth passage configured to
inject an additional oxidant into the chamber, and a sixth passage
configured to inject an additional diluent into the chamber,
wherein the fourth passage, the fifth passage, and the sixth
passage are fluidly isolated from each other along the additional
diffusion nozzle.
14. The system of claim 11, wherein the diffusion nozzle comprises
a fourth passage configured to inject an additional fuel, an
additional oxidant, or an additional diluent into the chamber,
wherein the fourth passage is fluidly isolated from the first
passage, the second passage, and the third passage along the
diffusion nozzle.
15. The system of claim 11, wherein the second passage is
configured to inject a mixture of the oxidant and an additional
diluent into the chamber.
16. The system of claim 11, comprising at least one valve or pump,
wherein the control system is configured to control the at least
one valve or pump of the system such that: the fuel is moved
through the first passage at the first flow rate based on the
system being operated at the full load, and the fuel is moved
through the first passage at the second flow rate based on the
system being operated at the partial load, wherein the second flow
rate differs from the first flow rate; or the oxidant is moved
through the second passage at the third flow rate based on the
system being operated at the full load, and the oxidant is moved
through the second passage at the fourth flow rate based on the
system being operated at the partial load, wherein the fourth flow
rate differs from the third flow rate; or the diluent is moved
through the third passage at the fifth flow rate based on the
system being operated at the full load, and the diluent is moved
through the third passage at the sixth flow rate based on the
system being operated at the partial load, wherein the sixth flow
rate differs from the fifth flow rate; or any combination
thereof.
17. A system, comprising: a turbine combustor comprising a chamber;
a first diffusion nozzle configured to inject a first fuel flow of
a first portion of fuel into the chamber of the turbine combustor,
a first oxidant flow of a first portion of oxidant into the chamber
of the turbine combustor, and a first diluent flow of a first
portion of diluent into the chamber of the turbine combustor,
wherein the first fuel flow, the first oxidant flow, and the first
diluent flow are fluidly separate from one another along the first
diffusion nozzle; a second diffusion nozzle configured to inject a
second fuel flow of a second portion of fuel into the chamber of
the turbine combustor, a second oxidant flow of a second portion of
oxidant into the chamber of the turbine combustor, and a second
diluent flow of a second portion of diluent into the chamber of the
turbine combustor, wherein the second fuel flow, the second oxidant
flow, and the second diluent flow are fluidly separate from one
another along the second diffusion nozzle; and a control system
configured to: change a first fuel flow rate of the first fuel
flow, a first oxidant flow rate of the first oxidant flow, a first
diluent flow rate of the first diluent flow, or any combination
thereof to correspond to a change of a load of the system from a
full load to a partial load; change a second fuel flow rate of the
second fuel flow, a second oxidant flow rate of the second oxidant
flow, a second diluent flow rate of the second diluent flow, or any
combination thereof to correspond to the change of the load of the
system from the full load to the partial load; and maintain a
stoichiometric ratio while the load of the system corresponds to
the full load and while the load of the system corresponds to the
partial load, wherein the stoichiometric ratio corresponds to an
equivalence ratio between 0.95 and 1.05.
18. The system of claim 17, comprising: a turbine configured to be
driven by combustion products generated from a diffusion flame
produced by the turbine combustor, wherein the turbine is
configured to output an exhaust gas; and an exhaust gas compressor
configured to compress the exhaust gas and route the exhaust gas
from the turbine, along an exhaust recirculation path, and to the
turbine combustor such that the exhaust gas forms: the first
diluent flow of the first portion of diluent; the second diluent
flow of the second portion of diluent; or both the first diluent
flow of the first portion of diluent and the second diluent flow of
the second portion of diluent.
19. The system of claim 17, comprising at least one valve or pump,
wherein the control system is configured to control the at least
one valve or pump to: change the first fuel flow rate of the first
fuel flow, the first oxidant flow rate of the first oxidant flow,
the first diluent flow rate of the first diluent flow, or any
combination thereof to correspond to the change of the load of the
system from the full load to the partial load; change the second
fuel flow rate of the second fuel flow, the second oxidant flow
rate of the second oxidant flow, the second diluent flow rate of
the second diluent flow, or any combination thereof to correspond
to the change of the load of the system from the full load to the
partial load; and maintain the stoichiometric ratio while the load
of the system corresponds to the full load and while the load of
the system corresponds to the partial load, wherein the
stoichiometric ratio corresponds to the equivalence ratio between
0.95 and 1.05.
20. The system of claim 17, wherein: the first diffusion nozzle is
configured to inject a third fuel flow of a third portion of fuel
into the chamber of the turbine combustor, a third oxidant flow of
a third portion of oxidant into the chamber of the turbine
combustor, or a third diluent flow of a third portion of diluent
into the chamber of the turbine combustor; and the second diffusion
nozzle is configured to inject a fourth fuel flow of a fourth
portion of fuel into the chamber of the turbine combustor, a fourth
oxidant flow of a fourth portion of oxidant into the chamber of the
turbine combustor, or a fourth diluent flow of a fourth portion of
diluent into the turbine combustor.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation of U.S. patent Ser. No.
16/284,746, entitled "SYSTEM AND METHOD FOR LOAD CONTROL WITH
DIFFUSION COMBUSTION IN A STOICHIOMETRIC EXHAUST GAS RECIRCULATION
GAS TURBINE SYSTEM," filed on Feb. 25, 2019, which is a
continuation of U.S. patent application Ser. No. 14/067,563, now
U.S. Pat. No. 10,215,412, entitled "SYSTEM AND METHOD FOR LOAD
CONTROL WITH DIFFUSION COMBUSTION IN A STOICHIOMETRIC EXHAUST GAS
RECIRCULATION GAS TURBINE SYSTEM," filed on Oct. 30, 2013, which
claims priority to and benefit of U.S. Provisional Patent
Application No. 61/722,118, entitled "SYSTEM AND METHOD FOR
DIFFUSION COMBUSTION IN A STOICHIOMETRIC EXHAUST GAS RECIRCULATION
GAS TURBINE SYSTEM," filed on Nov. 2, 2012, U.S. Provisional Patent
Application No. 61/722,115, entitled "SYSTEM AND METHOD FOR
DIFFUSION COMBUSTION WITH FUEL-DILUENT MIXING IN A STOICHIOMETRIC
EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEM," filed on Nov. 2,
2012, U.S. Provisional Patent Application No. 61/722,114, entitled
"SYSTEM AND METHOD FOR DIFFUSION COMBUSTION WITH OXIDANT-DILUENT
MIXING IN A STOICHIOMETRIC EXHAUST GAS RECIRCULATION GAS TURBINE
SYSTEM," filed on Nov. 2, 2012, and U.S. Provisional Patent
Application No. 61/722,111, entitled "SYSTEM AND METHOD FOR LOAD
CONTROL WITH DIFFUSION COMBUSTION IN A STOICHIOMETRIC EXHAUST GAS
RECIRCULATION GAS TURBINE SYSTEM," filed on Nov. 2, 2012, all of
which are herein incorporated by reference in their entirety for
all purposes.
BACKGROUND OF THE INVENTION
[0002] The subject matter disclosed herein relates to gas turbine
engines.
[0003] Gas turbine engines are used in a wide variety of
applications, such as power generation, aircraft, and various
machinery. Gas turbine engine generally combust a fuel with an
oxidant (e.g., air) in a combustor section to generate hot
combustion products, which then drive one or more turbine stages of
a turbine section. In turn, the turbine section drives one or more
compressor stages of a compressor section, thereby compressing
oxidant for intake into the combustor section along with the fuel.
Again, the fuel and oxidant mix in the combustor section, and then
combust to produce the hot combustion products. Gas turbine engines
generally premix the fuel and oxidant along one or more flow paths
upstream from a combustion chamber of the combustor section, and
thus gas turbine engines generally operate with premix flames.
Unfortunately, the premix flames may be difficult to control or
maintain, which can impact various exhaust emission and power
requirements. Furthermore, gas turbine engines typically consume a
vast amount of air as the oxidant, and output a considerable amount
of exhaust gas into the atmosphere. In other words, the exhaust gas
is typically wasted as a byproduct of the gas turbine
operation.
BRIEF DESCRIPTION OF THE INVENTION
[0004] Certain embodiments commensurate in scope with the
originally claimed invention are summarized below. These
embodiments are not intended to limit the scope of the claimed
invention, but rather these embodiments are intended only to
provide a brief summary of possible forms of the invention. Indeed,
the invention may encompass a variety of forms that may be similar
to or different from the embodiments set forth below.
[0005] In a first embodiment, a system is provided with a turbine
combustor having a first diffusion fuel nozzle, wherein the first
diffusion fuel nozzle is configured to produce a diffusion flame.
The system includes a turbine driven by combustion products from
the diffusion flame in the turbine combustor. The system also
includes an exhaust gas compressor, wherein the exhaust gas
compressor is configured to compress and route an exhaust gas from
the turbine to the turbine combustor along an exhaust recirculation
path. In addition, the system includes a control system configured
to control flow rates of at least one oxidant and at least one fuel
to the turbine combustor in a stoichiometric control mode and a
non-stoichiometric control mode, wherein the stoichiometric control
mode is configured to change the flow rates and provide a
substantially stoichiometric ratio of the at least one fuel with
the at least one oxidant, and the non-stoichiometric control mode
is configured to change the flow rates and provide a
non-stoichiometric ratio of the at least one fuel with the at least
one oxidant.
[0006] In a second embodiment, a method includes injecting at least
one oxidant and at least one fuel into a chamber of a turbine
combustor, wherein the at least one oxidant and the at least one
fuel mix and combust as a diffusion flame to generate combustion
products. The method further includes driving a turbine with the
combustion products and outputting an exhaust gas. The method
further includes recirculating the exhaust gas along an exhaust
recirculation path to an exhaust gas compressor. The method further
includes compressing and routing the exhaust gas to the turbine
combustor. The method further includes controlling flow rates of
the at least one oxidant and the at least one fuel to the turbine
combustor in a stoichiometric control mode, wherein the
stoichiometric control mode is configured to change the flow rates
and provide a substantially stoichiometric ratio of the at least
one fuel with the at least one oxidant. The method further includes
controlling flow rates of the at least one oxidant and the at least
one fuel to the turbine combustor in a non-stoichiometric control
mode, wherein the non-stoichiometric control mode is configured to
change the flow rates and provide a non-stoichiometric ratio of the
at least one fuel with the at least one oxidant.
[0007] In a third embodiment, a method includes introducing an
oxidant to at least one oxidant compressor to produce a compressed
oxidant stream. The method further includes introducing a
recirculated low oxygen content gas stream to a compressor section
of a gas turbine engine to produce a compressed low oxygen content
gas stream. The method further includes introducing a first portion
of the compressed oxidant stream with a first compressed oxidant
flow rate and a fuel stream with a first fuel flow rate in a
substantially stoichiometric ratio to at least one turbine
combustor and mixing the compressed oxidant stream and the fuel
stream at the point of combustion and combusting the mixture of the
compressed oxidant stream and the fuel stream. The method further
includes introducing a first portion of the compressed low oxygen
content gas stream with a low oxygen content gas flow rate to the
at least one turbine combustor and mixing it with the combusting
streams of compressed oxidant and fuel after the point of
combustion and producing a high temperature high pressure low
oxygen content stream. The method further includes introducing the
high temperature high pressure low oxygen content stream to an
expander section of the gas turbine engine and expanding the high
temperature high pressure low oxygen content stream to produce a
first mechanical power and a recirculated low oxygen content gas
stream at a first recirculated low oxygen content gas flow rate
wherein the recirculated low oxygen content gas stream contains a
first recirculated low oxygen content gas emissions level. The
method further includes using a first portion of the first
mechanical power to drive the compressor section of the gas turbine
engine. The method further includes using a second portion of the
first mechanical power to drive at least one of: a generator, the
at least one oxidant compressor or at least one other mechanical
device. The method further includes recirculating the recirculated
low oxygen content gas stream in a recirculation loop from the
outlet of the expander section to the inlet of the compressor
section of the gas turbine engine. The method further includes
extracting at least a second portion of the compressed low oxygen
content gas stream from the gas turbine engine and delivering the
at least a second portion of the compressed low oxygen content gas
stream to the first at least one oxidation catalyst unit and
producing a low oxygen content product stream comprising a first
low oxygen content product emissions level that is within a target
range. The method further includes reducing fuel stream flow rate
to a second fuel stream flow rate that is less than the first fuel
stream flow rate and reducing the first portion of the compressed
oxidant stream flow rate to a second compressed oxidant flow rate
that is less than the first compressed oxidant flow rate, wherein
the substantially stoichiometric ratio is maintained, producing a
second mechanical power that is less than the first mechanical
power and producing a low oxygen content product stream comprising
a second low oxygen content product emissions level that is within
a target range. The method further includes reducing fuel stream
flow rate to a third fuel stream flow rate that is less than the
second fuel stream flow rate and reducing the first portion of the
compressed oxidant stream flow rate to a third compressed oxidant
flow rate that is less than the second compressed oxidant flow
rate, wherein the substantially stoichiometric ratio is maintained,
producing a third mechanical power that is less than the second
mechanical power and producing a low oxygen content product stream
comprising a third low oxygen content product emissions level that
is at the limit of a target range. The method further includes
reducing fuel stream flow rate to a fourth fuel stream flow rate
that is less than the third fuel stream flow rate and reducing the
first portion of the compressed oxidant stream flow rate to a
fourth compressed oxidant flow rate that is less than the third
compressed oxidant flow rate, wherein the substantially
stoichiometric ratio is not maintained and fuel lean combustion is
achieved, producing a fourth mechanical power that is less than the
third mechanical power and producing a high oxygen content product
stream comprising a high oxygen content product emissions
level.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] These and other features, aspects, and advantages of the
present invention will become better understood when the following
detailed description is read with reference to the accompanying
drawings in which like characters represent like parts throughout
the drawings, wherein:
[0009] FIG. 1 is a diagram of an embodiment of a system having a
turbine-based service system coupled to a hydrocarbon production
system;
[0010] FIG. 2 is a diagram of an embodiment of the system of FIG.
1, further illustrating a control system and a combined cycle
system;
[0011] FIG. 3 is a diagram of an embodiment of the system of FIGS.
1 and 2, further illustrating details of a gas turbine engine,
exhaust gas supply system, and exhaust gas processing system;
[0012] FIG. 4 is a flow chart of an embodiment of a process for
operating the system of FIGS. 1-3;
[0013] FIG. 5 is a diagram of an embodiment of the exhaust gas
processing system of FIGS. 1-3;
[0014] FIG. 6 is a diagram of an embodiment of the exhaust gas
supply system of FIGS. 1-3;
[0015] FIG. 7 is a diagram of an embodiment of the gas turbine
engine of FIGS. 1-3, further illustrating details of the combustor,
fuel nozzle, and flows of oxidant, fuel, and diluent;
[0016] FIG. 8 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a premix fuel nozzle configuration;
[0017] FIG. 9 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a premix fuel nozzle configuration;
[0018] FIG. 10 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a premix fuel nozzle configuration;
[0019] FIG. 11 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a diffusion fuel nozzle configuration;
[0020] FIG. 12 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a diffusion fuel nozzle configuration;
[0021] FIG. 13 is a diagram of an embodiment of the fuel nozzle of
FIG. 7, illustrating a diffusion fuel nozzle configuration;
[0022] FIG. 14 is a schematic cross-section of an embodiment of the
fuel nozzle of FIG. 13, taken along line 14-14;
[0023] FIG. 15 is a schematic cross-section of an embodiment of the
fuel nozzle of FIG. 13, taken along line 14-14;
[0024] FIG. 16 is a diagram of an embodiment of the combustor and
fuel nozzle of FIG. 7, illustrating a diffusion fuel nozzle
configuration and a diluent injection system;
[0025] FIG. 17 is a schematic cross-section of an embodiment of the
combustor and fuel nozzles of FIG. 7, taken along line 17-17,
illustrating a multi-nozzle configuration of the fuel nozzles;
and
[0026] FIG. 18 is a graph of gas turbine load and exhaust gas
recirculation (EGR) flow versus fuel/oxidant ratio for a diffusion
flame configuration and a premix flame configuration.
DETAILED DESCRIPTION OF THE INVENTION
[0027] One or more specific embodiments of the present invention
will be described below. In an effort to provide a concise
description of these embodiments, all features of an actual
implementation may not be described in the specification. It should
be appreciated that in the development of any such actual
implementation, as in any engineering or design project, numerous
implementation-specific decisions must be made to achieve the
developers' specific goals, such as compliance with system-related
and business-related constraints, which may vary from one
implementation to another. Moreover, it should be appreciated that
such a development effort might be complex and time consuming, but
would nevertheless be a routine undertaking of design, fabrication,
and manufacture for those of ordinary skill having the benefit of
this disclosure.
[0028] When introducing elements of various embodiments of the
present invention, the articles "a," "an," "the," and "said" are
intended to mean that there are one or more of the elements. The
terms "comprising," "including," and "having" are intended to be
inclusive and mean that there may be additional elements other than
the listed elements.
[0029] As discussed in detail below, the disclosed embodiments
relate generally to gas turbine systems with exhaust gas
recirculation (EGR), and particularly stoichiometric operation of
the gas turbine systems using EGR. For example, the gas turbine
systems may be configured to recirculate the exhaust gas along an
exhaust recirculation path, stoichiometrically combust fuel and
oxidant along with at least some of the recirculated exhaust gas,
and capture the exhaust gas for use in various target systems. The
recirculation of the exhaust gas along with stoichiometric
combustion may help to increase the concentration level of carbon
dioxide (CO.sub.2) in the exhaust gas, which can then be post
treated to separate and purify the CO.sub.2 and nitrogen (N.sub.2)
for use in various target systems. The gas turbine systems also may
employ various exhaust gas processing (e.g., heat recovery,
catalyst reactions, etc.) along the exhaust recirculation path,
thereby increasing the concentration level of CO.sub.2, reducing
concentration levels of other emissions (e.g., carbon monoxide,
nitrogen oxides, and unburnt hydrocarbons), and increasing energy
recovery (e.g., with heat recovery units). Furthermore, the gas
turbine engines may be configured to combust the fuel and oxidant
with one or more diffusion flames, rather than or in addition to
premix flames. The diffusion flames may help to maintain stability
and operation within certain limits for stoichiometric combustion,
which in turn helps to increase production of CO.sub.2. For
example, as discussed below, a gas turbine system operating with
diffusion flames may enable a greater quantity of EGR, as compared
to a gas turbine system operating with premix flames. In turn, the
increased quantity of EGR helps to increase CO.sub.2 production.
Possible target systems include pipelines, storage tanks, carbon
sequestration systems, and hydrocarbon production systems, such as
enhanced oil recovery (EOR) systems.
[0030] As general context, it is noteworthy to discuss the
differences between a premix flame (i.e., premix combustion) versus
a diffusion flame (i.e., diffusion combustion). Combustion (i.e.,
premix or diffusion combustion) is essentially an exothermic
chemical reaction (e.g., combustion reaction) between a fuel and an
oxidant, such as air, oxygen, oxygen-enriched air, oxygen reduced
air, or mixtures of oxygen and nitrogen. The exothermic chemical
reaction between the fuel and the oxidant may substantially impact
(and control) the stability of the flame (e.g., the stability of
the flame surface), and vice versa. For example, the heat release
from the exothermic chemical reaction helps to sustain the flame,
and thus higher flame temperatures generally lead to greater flame
stability. In other words, higher temperatures associated with the
exothermic chemical reaction may help to increase flame stability,
whereas lower temperatures associated with the exothermic chemical
reaction may reduce the flame stability. The flame temperature may
be largely dependent on the fuel/oxidant ratio. In particular, the
flame temperature may be the greatest at a stoichiometric
fuel/oxidant ratio, which, as discussed in detail below, generally
involves an exothermic chemical reaction that consumes
substantially all of the fuel and oxidant, thereby resulting in
substantially no residual oxidant or unburnt fuel.
[0031] With premix combustion, the fuel and oxidant mix at one or
more locations upstream from the premix flame, which is essentially
a combustion of this pre-mixture of fuel and oxidant. In general,
the exothermic chemical reaction of fuel and oxidant in the premix
flame is constrained to the fuel/oxidant ratio of the pre-mixture,
which is achieved upstream from the premix flame. In many
configurations (particularly when one or more diluents are premixed
with the fuel and oxidant), it may be more difficult to maintain a
substantially stoichiometric fuel/oxidant ratio with a premix
flame, and thus it may be more difficult to maximize the stability
of the flame. In certain configurations, the premix flame may be
achieved with a fuel-lean fuel/oxidant ratio, which reduces the
flame temperature and, thus, helps to lower emissions of nitrogen
oxides (NO.sub.X), e.g., nitrogen monoxide (NO) and nitrogen
dioxide (NO.sub.2). While the reduced NO.sub.X emissions is
relevant for emissions regulations, the reduced flame temperature
also causes a reduction in flame stability. In the disclosed
embodiments, the system may be controlled to provide a
substantially stoichiometric fuel/oxidant ratio (e.g., increasing
flame temperature and flame stability), while using one or more
diluents to reduce the temperature for purposes of emissions
control (e.g., reducing NO.sub.X emissions). In particular, as
discussed below, the diluents may be provided separate from the
fuel and oxidant (e.g., after the point of combustion and/or
downstream from the premix flame), thereby enabling more precise
control of the fuel/oxidant ratio to achieve stoichiometric
combustion while also using the diluents to control the temperature
and emissions (e.g., NO.sub.X emissions). In other words, the fuel
and oxidant flows may be controlled independently from one another
and the diluent flow, thereby providing a more precisely controlled
fuel/oxidant ratio in the pre-mixture delivered to the location of
the premix flame.
[0032] With diffusion combustion, the fuel and oxidant generally do
not mix upstream from the diffusion flame, but rather the fuel and
oxidant mix and react directly at the flame surface and/or the
flame surface exists at the location of mixing between the fuel and
oxidant. In particular, the fuel and oxidant separately approach
the flame surface (or diffusion boundary/interface), and then
diffuse (e.g., via molecular and viscous diffusion) along the flame
surface (or diffusion boundary/interface) to generate the diffusion
flame. It is noteworthy that the fuel and oxidant may be at a
substantially stoichiometric ratio along this flame surface (or
diffusion boundary/interface), which may result in a greater flame
temperature (e.g., a peak flame temperature) along this flame
surface. Again, the stoichiometric fuel/oxidant ratio generally
results in a greater flame temperature (e.g., a peak flame
temperature), as compared with a fuel-lean or fuel-rich
fuel/oxidant ratio. As a result, the diffusion flame may be
substantially more stable than the premix flame, because the
diffusion of fuel and oxidant helps to maintain a stoichiometric
ratio (and greater temperature) along the flame surface. Although
greater flame temperatures can also lead to greater exhaust
emissions, such as NO.sub.X emissions, the disclosed embodiments
use one or more diluents to help control the temperature and
emissions while still avoiding any premixing of the fuel and
oxidant. For example, the disclosed embodiments may introduce one
or more diluents separate from the fuel and oxidant (e.g., after
the point of combustion and/or downstream from the diffusion
flame), thereby helping to reduce the temperature and reduce the
emissions (e.g., NO.sub.X emissions) produced by the diffusion
flame.
[0033] In the disclosed embodiments, the exhaust gas provided by
the exhaust gas recirculation (EGR) serves as at least one of the
diluents. The exhaust gas (as one of the diluents) is essentially
decoupled from the flows of oxidant and fuel, thereby enabling
independent control of the fuel, oxidant, and diluent (e.g.,
exhaust gas) flows. In certain embodiments, the exhaust gas may be
injected into the turbine combustor after the point of combustion
and/or downstream from the flame (e.g., premix flame and/or
diffusion flame), thereby helping to reduce the temperature and
reduce exhaust emissions, e.g., NO.sub.X emissions. However, other
diluents (e.g., steam, nitrogen, or other inert gases) also may be
used for temperature and/or emissions control, alone or in
combination with the exhaust gas. Given the differences between
premix flames and diffusion flames, the amount of EGR may vary
considerably between a gas turbine system operating with premix
fuel nozzles versus diffusion fuel nozzles. A premix flame may be
constrained to the pre-mixture upstream from the premix flame
(e.g., including mixing of the diluent with the fuel and oxidant),
and thus, the premix flame may not be capable of maintaining flame
stability above a certain level of EGR. In other words, in a premix
flame configuration of the gas turbine system, an increasing amount
of exhaust gas (e.g., EGR) that premixes with the fuel and oxidant
may increasingly reduce the temperature and flame stability of the
premix flame, and thus too much EGR may cause the premix flame to
become unstable. However, in a diffusion flame configuration of the
gas turbine system, it is now believed that an increasing amount of
exhaust gas (e.g., EGR) can be used along with the diffusion flame,
well beyond any limits associated with a premix flame
configuration. For example, in a substantially stoichiometric EGR
gas turbine system, the amount of exhaust gas (e.g., EGR) that may
be used with a diffusion flame configuration may be at least
approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, or 100 percent
greater than the amount of exhaust gas (e.g., EGR) that may be used
with a premix flame configuration. By further example, in a
substantially stoichiometric EGR gas turbine system, the amount of
exhaust gas (e.g., EGR) that may be used with a diffusion flame
configuration may be greater than approximately 35, 40, 45, 50, 55,
60, 65, 70, or 75 percent by volume of the exhaust gas (e.g., EGR)
relative to the total flow through the combustors and turbine
section (e.g., total flow of oxidant, fuel, and diluents). As a
result, a significant improvement in CO.sub.2 production may be
achieved by using diffusion flames (e.g., diffusion fuel nozzles)
along with a substantially stoichiometric EGR gas turbine
system.
[0034] Although the diffusion fuel nozzles may be particularly
helpful in increasing quantities of EGR and CO.sub.2 production,
the disclosed embodiments employ various controls to help control
the fuel/oxidant ratio, the stability of the flame, exhaust
emissions, and power output, whether the system is operating with a
premix flame, a diffusion flame, or a combination thereof. For
example, the disclosed embodiments may include combustors with one
or more diffusion fuel nozzles and premix fuel nozzles, which may
be independently controlled through different fluid supply circuits
to provide benefits of both premix flame configurations and
diffusion flame configurations.
[0035] FIG. 1 is a diagram of an embodiment of a system 10 having
an hydrocarbon production system 12 associated with a turbine-based
service system 14. As discussed in further detail below, various
embodiments of the turbine-based service system 14 are configured
to provide various services, such as electrical power, mechanical
power, and fluids (e.g., exhaust gas), to the hydrocarbon
production system 12 to facilitate the production or retrieval of
oil and/or gas. In the illustrated embodiment, the hydrocarbon
production system 12 includes an oil/gas extraction system 16 and
an enhanced oil recovery (EOR) system 18, which are coupled to a
subterranean reservoir 20 (e.g., an oil, gas, or hydrocarbon
reservoir). The oil/gas extraction system 16 includes a variety of
surface equipment 22, such as a Christmas tree or production tree
24, coupled to an oil/gas well 26. Furthermore, the well 26 may
include one or more tubulars 28 extending through a drilled bore 30
in the earth 32 to the subterranean reservoir 20. The tree 24
includes one or more valves, chokes, isolation sleeves, blowout
preventers, and various flow control devices, which regulate
pressures and control flows to and from the subterranean reservoir
20. While the tree 24 is generally used to control the flow of the
production fluid (e.g., oil or gas) out of the subterranean
reservoir 20, the EOR system 18 may increase the production of oil
or gas by injecting one or more fluids into the subterranean
reservoir 20.
[0036] Accordingly, the EOR system 18 may include a fluid injection
system 34, which has one or more tubulars 36 extending through a
bore 38 in the earth 32 to the subterranean reservoir 20. For
example, the EOR system 18 may route one or more fluids 40, such as
gas, steam, water, chemicals, or any combination thereof, into the
fluid injection system 34. For example, as discussed in further
detail below, the EOR system 18 may be coupled to the turbine-based
service system 14, such that the system 14 routes an exhaust gas 42
(e.g., substantially or entirely free of oxygen) to the EOR system
18 for use as the injection fluid 40. The fluid injection system 34
routes the fluid 40 (e.g., the exhaust gas 42) through the one or
more tubulars 36 into the subterranean reservoir 20, as indicated
by arrows 44. The injection fluid 40 enters the subterranean
reservoir 20 through the tubular 36 at an offset distance 46 away
from the tubular 28 of the oil/gas well 26. Accordingly, the
injection fluid 40 displaces the oil/gas 48 disposed in the
subterranean reservoir 20, and drives the oil/gas 48 up through the
one or more tubulars 28 of the hydrocarbon production system 12, as
indicated by arrows 50. As discussed in further detail below, the
injection fluid 40 may include the exhaust gas 42 originating from
the turbine-based service system 14, which is able to generate the
exhaust gas 42 on-site as needed by the hydrocarbon production
system 12. In other words, the turbine-based system 14 may
simultaneously generate one or more services (e.g., electrical
power, mechanical power, steam, water (e.g., desalinated water),
and exhaust gas (e.g., substantially free of oxygen)) for use by
the hydrocarbon production system 12, thereby reducing or
eliminating the reliance on external sources of such services.
[0037] In the illustrated embodiment, the turbine-based service
system 14 includes a stoichiometric exhaust gas recirculation
(SEGR) gas turbine system 52 and an exhaust gas (EG) processing
system 54. The gas turbine system 52 may be configured to operate
in a stoichiometric combustion mode of operation (e.g., a
stoichiometric control mode) and a non-stoichiometric combustion
mode of operation (e.g., a non-stoichiometric control mode), such
as a fuel-lean control mode or a fuel-rich control mode. In the
stoichiometric control mode, the combustion generally occurs in a
substantially stoichiometric ratio of a fuel and oxidant, thereby
resulting in substantially stoichiometric combustion. In
particular, stoichiometric combustion generally involves consuming
substantially all of the fuel and oxidant in the combustion
reaction, such that the products of combustion are substantially or
entirely free of unburnt fuel and oxidant. One measure of
stoichiometric combustion is the equivalence ratio, or phi (.PHI.),
which is the ratio of the actual fuel/oxidant ratio relative to the
stoichiometric fuel/oxidant ratio. An equivalence ratio of greater
than 1.0 results in a fuel-rich combustion of the fuel and oxidant,
whereas an equivalence ratio of less than 1.0 results in a
fuel-lean combustion of the fuel and oxidant. In contrast, an
equivalence ratio of 1.0 results in combustion that is neither
fuel-rich nor fuel-lean, thereby substantially consuming all of the
fuel and oxidant in the combustion reaction. In context of the
disclosed embodiments, the term stoichiometric or substantially
stoichiometric may refer to an equivalence ratio of approximately
0.95 to approximately 1.05. However, the disclosed embodiments may
also include an equivalence ratio of 1.0 plus or minus 0.01, 0.02,
0.03, 0.04, 0.05, or more. Again, the stoichiometric combustion of
fuel and oxidant in the turbine-based service system 14 may result
in products of combustion or exhaust gas (e.g., 42) with
substantially no unburnt fuel or oxidant remaining. For example,
the exhaust gas 42 may have less than 1, 2, 3, 4, or 5 percent by
volume of oxidant (e.g., oxygen), unburnt fuel or hydrocarbons
(e.g., HCs), nitrogen oxides (e.g., NO.sub.X), carbon monoxide
(CO), sulfur oxides (e.g., SO.sub.X), hydrogen, and other products
of incomplete combustion. By further example, the exhaust gas 42
may have less than approximately 10, 20, 30, 40, 50, 60, 70, 80,
90, 100, 200, 300, 400, 500, 1000, 2000, 3000, 4000, or 5000 parts
per million by volume (ppmv) of oxidant (e.g., oxygen), unburnt
fuel or hydrocarbons (e.g., HCs), nitrogen oxides (e.g., NO.sub.X),
carbon monoxide (CO), sulfur oxides (e.g., SO.sub.X), hydrogen, and
other products of incomplete combustion. However, the disclosed
embodiments also may produce other ranges of residual fuel,
oxidant, and other emissions levels in the exhaust gas 42. As used
herein, the terms emissions, emissions levels, and emissions
targets may refer to concentration levels of certain products of
combustion (e.g., NO.sub.X, CO, SO.sub.X, O.sub.2, N.sub.2,
H.sub.2, HCs, etc.), which may be present in recirculated gas
streams, vented gas streams (e.g., exhausted into the atmosphere),
and gas streams used in various target systems (e.g., the
hydrocarbon production system 12).
[0038] Although the SEGR gas turbine system 52 and the EG
processing system 54 may include a variety of components in
different embodiments, the illustrated EG processing system 54
includes a heat recovery steam generator (HRSG) 56 and an exhaust
gas recirculation (EGR) system 58, which receive and process an
exhaust gas 60 originating from the SEGR gas turbine system 52. The
HRSG 56 may include one or more heat exchangers, condensers, and
various heat recovery equipment, which collectively function to
transfer heat from the exhaust gas 60 to a stream of water, thereby
generating steam 62. The steam 62 may be used in one or more steam
turbines, the EOR system 18, or any other portion of the
hydrocarbon production system 12. For example, the HRSG 56 may
generate low pressure, medium pressure, and/or high pressure steam
62, which may be selectively applied to low, medium, and high
pressure steam turbine stages, or different applications of the EOR
system 18. In addition to the steam 62, a treated water 64, such as
a desalinated water, may be generated by the HRSG 56, the EGR
system 58, and/or another portion of the EG processing system 54 or
the SEGR gas turbine system 52. The treated water 64 (e.g.,
desalinated water) may be particularly useful in areas with water
shortages, such as inland or desert regions. The treated water 64
may be generated, at least in part, due to the large volume of air
driving combustion of fuel within the SEGR gas turbine system 52.
While the on-site generation of steam 62 and water 64 may be
beneficial in many applications (including the hydrocarbon
production system 12), the on-site generation of exhaust gas 42, 60
may be particularly beneficial for the EOR system 18, due to its
low oxygen content, high pressure, and heat derived from the SEGR
gas turbine system 52. Accordingly, the HRSG 56, the EGR system 58,
and/or another portion of the EG processing system 54 may output or
recirculate an exhaust gas 66 into the SEGR gas turbine system 52,
while also routing the exhaust gas 42 to the EOR system 18 for use
with the hydrocarbon production system 12. Likewise, the exhaust
gas 42 may be extracted directly from the SEGR gas turbine system
52 (i.e., without passing through the EG processing system 54) for
use in the EOR system 18 of the hydrocarbon production system
12.
[0039] The exhaust gas recirculation is handled by the EGR system
58 of the EG processing system 54. For example, the EGR system 58
includes one or more conduits, valves, blowers, exhaust gas
treatment systems (e.g., filters, particulate removal units, gas
separation units, gas purification units, heat exchangers, heat
recovery units, moisture removal units, catalyst units, chemical
injection units, or any combination thereof), and controls to
recirculate the exhaust gas along an exhaust gas circulation path
from an output (e.g., discharged exhaust gas 60) to an input (e.g.,
intake exhaust gas 66) of the SEGR gas turbine system 52. In the
illustrated embodiment, the SEGR gas turbine system 52 intakes the
exhaust gas 66 into a compressor section having one or more
compressors, thereby compressing the exhaust gas 66 for use in a
combustor section along with an intake of an oxidant 68 and one or
more fuels 70. The oxidant 68 may include ambient air, pure oxygen,
oxygen-enriched air, oxygen-reduced air, oxygen-nitrogen mixtures,
or any suitable oxidant that facilitates combustion of the fuel 70.
The fuel 70 may include one or more gas fuels, liquid fuels, or any
combination thereof. For example, the fuel 70 may include natural
gas, liquefied natural gas (LNG), syngas, methane, ethane, propane,
butane, naphtha, kerosene, diesel fuel, ethanol, methanol, biofuel,
or any combination thereof.
[0040] The SEGR gas turbine system 52 mixes and combusts the
exhaust gas 66, the oxidant 68, and the fuel 70 in the combustor
section, thereby generating hot combustion gases or exhaust gas 60
to drive one or more turbine stages in a turbine section. In
certain embodiments, each combustor in the combustor section
includes one or more premix fuel nozzles, one or more diffusion
fuel nozzles, or any combination thereof. For example, each premix
fuel nozzle may be configured to mix the oxidant 68 and the fuel 70
internally within the fuel nozzle and/or partially upstream of the
fuel nozzle, thereby injecting an oxidant-fuel mixture from the
fuel nozzle into the combustion zone for a premixed combustion
(e.g., a premixed flame). By further example, each diffusion fuel
nozzle may be configured to isolate the flows of oxidant 68 and
fuel 70 within the fuel nozzle, thereby separately injecting the
oxidant 68 and the fuel 70 from the fuel nozzle into the combustion
zone for diffusion combustion (e.g., a diffusion flame). In
particular, the diffusion combustion provided by the diffusion fuel
nozzles delays mixing of the oxidant 68 and the fuel 70 until the
point of initial combustion, i.e., the flame region. In embodiments
employing the diffusion fuel nozzles, the diffusion flame may
provide increased flame stability, because the diffusion flame
generally forms at the point of stoichiometry between the separate
streams of oxidant 68 and fuel 70 (i.e., as the oxidant 68 and fuel
70 are mixing). In certain embodiments, one or more diluents (e.g.,
the exhaust gas 60, steam, nitrogen, or another inert gas) may be
pre-mixed with the oxidant 68, the fuel 70, or both, in either the
diffusion fuel nozzle or the premix fuel nozzle. In addition, one
or more diluents (e.g., the exhaust gas 60, steam, nitrogen, or
another inert gas) may be injected into the combustor at or
downstream from the point of combustion within each combustor. The
use of these diluents may help temper the flame (e.g., premix flame
or diffusion flame), thereby helping to reduce NO.sub.X emissions,
such as nitrogen monoxide (NO) and nitrogen dioxide (NO.sub.2).
Regardless of the type of flame, the combustion produces hot
combustion gases or exhaust gas 60 to drive one or more turbine
stages. As each turbine stage is driven by the exhaust gas 60, the
SEGR gas turbine system 52 generates a mechanical power 72 and/or
an electrical power 74 (e.g., via an electrical generator). The
system 52 also outputs the exhaust gas 60, and may further output
water 64. Again, the water 64 may be a treated water, such as a
desalinated water, which may be useful in a variety of applications
on-site or off-site.
[0041] Exhaust extraction is also provided by the SEGR gas turbine
system 52 using one or more extraction points 76. For example, the
illustrated embodiment includes an exhaust gas (EG) supply system
78 having an exhaust gas (EG) extraction system 80 and an exhaust
gas (EG) treatment system 82, which receive exhaust gas 42 from the
extraction points 76, treat the exhaust gas 42, and then supply or
distribute the exhaust gas 42 to various target systems. The target
systems may include the EOR system 18 and/or other systems, such as
a pipeline 86, a storage tank 88, or a carbon sequestration system
90. The EG extraction system 80 may include one or more conduits,
valves, controls, and flow separations, which facilitate isolation
of the exhaust gas 42 from the oxidant 68, the fuel 70, and other
contaminants, while also controlling the temperature, pressure, and
flow rate of the extracted exhaust gas 42. The EG treatment system
82 may include one or more heat exchangers (e.g., heat recovery
units such as heat recovery steam generators, condensers, coolers,
or heaters), catalyst systems (e.g., oxidation catalyst systems),
particulate and/or water removal systems (e.g., gas dehydration
units, inertial separators, coalescing filters, water impermeable
filters, and other filters), chemical injection systems, solvent
based treatment systems (e.g., absorbers, flash tanks, etc.),
carbon capture systems, gas separation systems, gas purification
systems, and/or a solvent based treatment system, exhaust gas
compressors, any combination thereof. These subsystems of the EG
treatment system 82 enable control of the temperature, pressure,
flow rate, moisture content (e.g., amount of water removal),
particulate content (e.g., amount of particulate removal), and gas
composition (e.g., percentage of CO.sub.2, N.sub.2, etc.).
[0042] The extracted exhaust gas 42 is treated by one or more
subsystems of the EG treatment system 82, depending on the target
system. For example, the EG treatment system 82 may direct all or
part of the exhaust gas 42 through a carbon capture system, a gas
separation system, a gas purification system, and/or a solvent
based treatment system, which is controlled to separate and purify
a carbonaceous gas (e.g., carbon dioxide) 92 and/or nitrogen
(N.sub.2) 94 for use in the various target systems. For example,
embodiments of the EG treatment system 82 may perform gas
separation and purification to produce a plurality of different
streams 95 of exhaust gas 42, such as a first stream 96, a second
stream 97, and a third stream 98. The first stream 96 may have a
first composition that is rich in carbon dioxide and/or lean in
nitrogen (e.g., a CO.sub.2 rich, N.sub.2 lean stream). The second
stream 97 may have a second composition that has intermediate
concentration levels of carbon dioxide and/or nitrogen (e.g.,
intermediate concentration CO.sub.2, N.sub.2 stream). The third
stream 98 may have a third composition that is lean in carbon
dioxide and/or rich in nitrogen (e.g., a CO.sub.2 lean, N.sub.2
rich stream). Each stream 95 (e.g., 96, 97, and 98) may include a
gas dehydration unit, a filter, a gas compressor, or any
combination thereof, to facilitate delivery of the stream 95 to a
target system. In certain embodiments, the CO.sub.2 rich, N.sub.2
lean stream 96 may have a CO.sub.2 purity or concentration level of
greater than approximately 70, 75, 80, 85, 90, 95, 96, 97, 98, or
99 percent by volume, and a N.sub.2 purity or concentration level
of less than approximately 1, 2, 3, 4, 5, 10, 15, 20, 25, or 30
percent by volume. In contrast, the CO.sub.2 lean, N.sub.2 rich
stream 98 may have a CO.sub.2 purity or concentration level of less
than approximately 1, 2, 3, 4, 5, 10, 15, 20, 25, or 30 percent by
volume, and a N.sub.2 purity or concentration level of greater than
approximately 70, 75, 80, 85, 90, 95, 96, 97, 98, or 99 percent by
volume. The intermediate concentration CO.sub.2, N.sub.2 stream 97
may have a CO.sub.2 purity or concentration level and/or a N.sub.2
purity or concentration level of between approximately 30 to 70, 35
to 65, 40 to 60, or 45 to 55 percent by volume. Although the
foregoing ranges are merely non-limiting examples, the CO.sub.2
rich, N.sub.2 lean stream 96 and the CO.sub.2 lean, N.sub.2 rich
stream 98 may be particularly well suited for use with the EOR
system 18 and the other systems 84. However, any of these rich,
lean, or intermediate concentration CO.sub.2 streams 95 may be
used, alone or in various combinations, with the EOR system 18 and
the other systems 84. For example, the EOR system 18 and the other
systems 84 (e.g., the pipeline 86, storage tank 88, and the carbon
sequestration system 90) each may receive one or more CO.sub.2
rich, N.sub.2 lean streams 96, one or more CO.sub.2 lean, N.sub.2
rich streams 98, one or more intermediate concentration CO.sub.2,
N.sub.2 streams 97, and one or more untreated exhaust gas 42
streams (i.e., bypassing the EG treatment system 82).
[0043] The EG extraction system 80 extracts the exhaust gas 42 at
one or more extraction points 76 along the compressor section, the
combustor section, and/or the turbine section, such that the
exhaust gas 42 may be used in the EOR system 18 and other systems
84 at suitable temperatures and pressures. The EG extraction system
80 and/or the EG treatment system 82 also may circulate fluid flows
(e.g., exhaust gas 42) to and from the EG processing system 54. For
example, a portion of the exhaust gas 42 passing through the EG
processing system 54 may be extracted by the EG extraction system
80 for use in the EOR system 18 and the other systems 84. In
certain embodiments, the EG supply system 78 and the EG processing
system 54 may be independent or integral with one another, and thus
may use independent or common subsystems. For example, the EG
treatment system 82 may be used by both the EG supply system 78 and
the EG processing system 54. Exhaust gas 42 extracted from the EG
processing system 54 may undergo multiple stages of gas treatment,
such as one or more stages of gas treatment in the EG processing
system 54 followed by one or more additional stages of gas
treatment in the EG treatment system 82.
[0044] At each extraction point 76, the extracted exhaust gas 42
may be substantially free of oxidant 68 and fuel 70 (e.g., unburnt
fuel or hydrocarbons) due to substantially stoichiometric
combustion and/or gas treatment in the EG processing system 54.
Furthermore, depending on the target system, the extracted exhaust
gas 42 may undergo further treatment in the EG treatment system 82
of the EG supply system 78, thereby further reducing any residual
oxidant 68, fuel 70, or other undesirable products of combustion.
For example, either before or after treatment in the EG treatment
system 82, the extracted exhaust gas 42 may have less than 1, 2, 3,
4, or 5 percent by volume of oxidant (e.g., oxygen), unburnt fuel
or hydrocarbons (e.g., HCs), nitrogen oxides (e.g., NO.sub.X),
carbon monoxide (CO), sulfur oxides (e.g., SO.sub.X), hydrogen, and
other products of incomplete combustion. By further example, either
before or after treatment in the EG treatment system 82, the
extracted exhaust gas 42 may have less than approximately 10, 20,
30, 40, 50, 60, 70, 80, 90, 100, 200, 300, 400, 500, 1000, 2000,
3000, 4000, or 5000 parts per million by volume (ppmv) of oxidant
(e.g., oxygen), unburnt fuel or hydrocarbons (e.g., HCs), nitrogen
oxides (e.g., NO.sub.X), carbon monoxide (CO), sulfur oxides (e.g.,
SO.sub.X), hydrogen, and other products of incomplete combustion.
Thus, the exhaust gas 42 is particularly well suited for use with
the EOR system 18.
[0045] The EGR operation of the turbine system 52 specifically
enables the exhaust extraction at a multitude of locations 76. For
example, the compressor section of the system 52 may be used to
compress the exhaust gas 66 without any oxidant 68 (i.e., only
compression of the exhaust gas 66), such that a substantially
oxygen-free exhaust gas 42 may be extracted from the compressor
section and/or the combustor section prior to entry of the oxidant
68 and the fuel 70. The extraction points 76 may be located at
interstage ports between adjacent compressor stages, at ports along
the compressor discharge casing, at ports along each combustor in
the combustor section, or any combination thereof. In certain
embodiments, the exhaust gas 66 may not mix with the oxidant 68 and
fuel 70 until it reaches the head end portion and/or fuel nozzles
of each combustor in the combustor section. Furthermore, one or
more flow separators (e.g., walls, dividers, baffles, or the like)
may be used to isolate the oxidant 68 and the fuel 70 from the
extraction points 76. With these flow separators, the extraction
points 76 may be disposed directly along a wall of each combustor
in the combustor section.
[0046] Once the exhaust gas 66, oxidant 68, and fuel 70 flow
through the head end portion (e.g., through fuel nozzles) into the
combustion portion (e.g., combustion chamber) of each combustor,
the SEGR gas turbine system 52 is controlled to provide a
substantially stoichiometric combustion of the exhaust gas 66,
oxidant 68, and fuel 70. For example, the system 52 may maintain an
equivalence ratio of approximately 0.95 to approximately 1.05. As a
result, the products of combustion of the mixture of exhaust gas
66, oxidant 68, and fuel 70 in each combustor is substantially free
of oxygen and unburnt fuel. Thus, the products of combustion (or
exhaust gas) may be extracted from the turbine section of the SEGR
gas turbine system 52 for use as the exhaust gas 42 routed to the
EOR system 18. Along the turbine section, the extraction points 76
may be located at any turbine stage, such as interstage ports
between adjacent turbine stages. Thus, using any of the foregoing
extraction points 76, the turbine-based service system 14 may
generate, extract, and deliver the exhaust gas 42 to the
hydrocarbon production system 12 (e.g., the EOR system 18) for use
in the production of oil/gas 48 from the subterranean reservoir
20.
[0047] FIG. 2 is a diagram of an embodiment of the system 10 of
FIG. 1, illustrating a control system 100 coupled to the
turbine-based service system 14 and the hydrocarbon production
system 12. In the illustrated embodiment, the turbine-based service
system 14 includes a combined cycle system 102, which includes the
SEGR gas turbine system 52 as a topping cycle, a steam turbine 104
as a bottoming cycle, and the HRSG 56 to recover heat from the
exhaust gas 60 to generate the steam 62 for driving the steam
turbine 104. Again, the SEGR gas turbine system 52 receives, mixes,
and stoichiometrically combusts the exhaust gas 66, the oxidant 68,
and the fuel 70 (e.g., premix and/or diffusion flames), thereby
producing the exhaust gas 60, the mechanical power 72, the
electrical power 74, and/or the water 64. For example, the SEGR gas
turbine system 52 may drive one or more loads or machinery 106,
such as an electrical generator, an oxidant compressor (e.g., a
main air compressor), a gear box, a pump, equipment of the
hydrocarbon production system 12, or any combination thereof. In
some embodiments, the machinery 106 may include other drives, such
as electrical motors or steam turbines (e.g., the steam turbine
104), in tandem with the SEGR gas turbine system 52. Accordingly,
an output of the machinery 106 driven by the SEGR gas turbines
system 52 (and any additional drives) may include the mechanical
power 72 and the electrical power 74. The mechanical power 72
and/or the electrical power 74 may be used on-site for powering the
hydrocarbon production system 12, the electrical power 74 may be
distributed to the power grid, or any combination thereof. The
output of the machinery 106 also may include a compressed fluid,
such as a compressed oxidant 68 (e.g., air or oxygen), for intake
into the combustion section of the SEGR gas turbine system 52. Each
of these outputs (e.g., the exhaust gas 60, the mechanical power
72, the electrical power 74, and/or the water 64) may be considered
a service of the turbine-based service system 14.
[0048] The SEGR gas turbine system 52 produces the exhaust gas 42,
60, which may be substantially free of oxygen, and routes this
exhaust gas 42, 60 to the EG processing system 54 and/or the EG
supply system 78. The EG supply system 78 may treat and delivery
the exhaust gas 42 (e.g., streams 95) to the hydrocarbon production
system 12 and/or the other systems 84. As discussed above, the EG
processing system 54 may include the HRSG 56 and the EGR system 58.
The HRSG 56 may include one or more heat exchangers, condensers,
and various heat recovery equipment, which may be used to recover
or transfer heat from the exhaust gas 60 to water 108 to generate
the steam 62 for driving the steam turbine 104. Similar to the SEGR
gas turbine system 52, the steam turbine 104 may drive one or more
loads or machinery 106, thereby generating the mechanical power 72
and the electrical power 74. In the illustrated embodiment, the
SEGR gas turbine system 52 and the steam turbine 104 are arranged
in tandem to drive the same machinery 106. However, in other
embodiments, the SEGR gas turbine system 52 and the steam turbine
104 may separately drive different machinery 106 to independently
generate mechanical power 72 and/or electrical power 74. As the
steam turbine 104 is driven by the steam 62 from the HRSG 56, the
steam 62 gradually decreases in temperature and pressure.
Accordingly, the steam turbine 104 recirculates the used steam 62
and/or water 108 back into the HRSG 56 for additional steam
generation via heat recovery from the exhaust gas 60. In addition
to steam generation, the HRSG 56, the EGR system 58, and/or another
portion of the EG processing system 54 may produce the water 64,
the exhaust gas 42 for use with the hydrocarbon production system
12, and the exhaust gas 66 for use as an input into the SEGR gas
turbine system 52. For example, the water 64 may be a treated water
64, such as a desalinated water for use in other applications. The
desalinated water may be particularly useful in regions of low
water availability. Regarding the exhaust gas 60, embodiments of
the EG processing system 54 may be configured to recirculate the
exhaust gas 60 through the EGR system 58 with or without passing
the exhaust gas 60 through the HRSG 56.
[0049] In the illustrated embodiment, the SEGR gas turbine system
52 has an exhaust recirculation path 110, which extends from an
exhaust outlet to an exhaust inlet of the system 52. Along the path
110, the exhaust gas 60 passes through the EG processing system 54,
which includes the HRSG 56 and the EGR system 58 in the illustrated
embodiment. The EGR system 58 may include one or more conduits,
valves, blowers, gas treatment systems (e.g., filters, particulate
removal units, gas separation units, gas purification units, heat
exchangers, heat recovery units such as heat recovery steam
generators, moisture removal units, catalyst units, chemical
injection units, or any combination thereof) in series and/or
parallel arrangements along the path 110. In other words, the EGR
system 58 may include any flow control components, pressure control
components, temperature control components, moisture control
components, and gas composition control components along the
exhaust recirculation path 110 between the exhaust outlet and the
exhaust inlet of the system 52. Accordingly, in embodiments with
the HRSG 56 along the path 110, the HRSG 56 may be considered a
component of the EGR system 58. However, in certain embodiments,
the HRSG 56 may be disposed along an exhaust path independent from
the exhaust recirculation path 110. Regardless of whether the HRSG
56 is along a separate path or a common path with the EGR system
58, the HRSG 56 and the EGR system 58 intake the exhaust gas 60 and
output either the recirculated exhaust gas 66, the exhaust gas 42
for use with the EG supply system 78 (e.g., for the hydrocarbon
production system 12 and/or other systems 84), or another output of
exhaust gas. Again, the SEGR gas turbine system 52 intakes, mixes,
and stoichiometrically combusts the exhaust gas 66, the oxidant 68,
and the fuel 70 (e.g., premixed and/or diffusion flames) to produce
a substantially oxygen-free and fuel-free exhaust gas 60 for
distribution to the EG processing system 54, the hydrocarbon
production system 12, or other systems 84.
[0050] As noted above with reference to FIG. 1, the hydrocarbon
production system 12 may include a variety of equipment to
facilitate the recovery or production of oil/gas 48 from a
subterranean reservoir 20 through an oil/gas well 26. For example,
the hydrocarbon production system 12 may include the EOR system 18
having the fluid injection system 34. In the illustrated
embodiment, the fluid injection system 34 includes an exhaust gas
injection EOR system 112 and a steam injection EOR system 114.
Although the fluid injection system 34 may receive fluids from a
variety of sources, the illustrated embodiment may receive the
exhaust gas 42 and the steam 62 from the turbine-based service
system 14. The exhaust gas 42 and/or the steam 62 produced by the
turbine-based service system 14 also may be routed to the
hydrocarbon production system 12 for use in other oil/gas systems
116.
[0051] The quantity, quality, and flow of the exhaust gas 42 and/or
the steam 62 may be controlled by the control system 100. The
control system 100 may be dedicated entirely to the turbine-based
service system 14, or the control system 100 may optionally also
provide control (or at least some data to facilitate control) for
the hydrocarbon production system 12 and/or other systems 84. In
the illustrated embodiment, the control system 100 includes a
controller 118 having a processor 120, a memory 122, a steam
turbine control 124, a SEGR gas turbine system control 126, and a
machinery control 128. The processor 120 may include a single
processor or two or more redundant processors, such as triple
redundant processors for control of the turbine-based service
system 14. The memory 122 may include volatile and/or non-volatile
memory. For example, the memory 122 may include one or more hard
drives, flash memory, read-only memory, random access memory, or
any combination thereof. The controls 124, 126, and 128 may include
software and/or hardware controls. For example, the controls 124,
126, and 128 may include various instructions or code stored on the
memory 122 and executable by the processor 120. The control 124 is
configured to control operation of the steam turbine 104, the SEGR
gas turbine system control 126 is configured to control the system
52, and the machinery control 128 is configured to control the
machinery 106. Thus, the controller 118 (e.g., controls 124, 126,
and 128) may be configured to coordinate various sub-systems of the
turbine-based service system 14 to provide a suitable stream of the
exhaust gas 42 to the hydrocarbon production system 12.
[0052] In certain embodiments of the control system 100, each
element (e.g., system, subsystem, and component) illustrated in the
drawings or described herein includes (e.g., directly within,
upstream, or downstream of such element) one or more industrial
control features, such as sensors and control devices, which are
communicatively coupled with one another over an industrial control
network along with the controller 118. For example, the control
devices associated with each element may include a dedicated device
controller (e.g., including a processor, memory, and control
instructions), one or more actuators, valves, switches, and
industrial control equipment, which enable control based on sensor
feedback 130, control signals from the controller 118, control
signals from a user, or any combination thereof. Thus, any of the
control functionality described herein may be implemented with
control instructions stored and/or executable by the controller
118, dedicated device controllers associated with each element, or
a combination thereof.
[0053] In order to facilitate such control functionality, the
control system 100 includes one or more sensors distributed
throughout the system 10 to obtain the sensor feedback 130 for use
in execution of the various controls, e.g., the controls 124, 126,
and 128. For example, the sensor feedback 130 may be obtained from
sensors distributed throughout the SEGR gas turbine system 52, the
machinery 106, the EG processing system 54, the steam turbine 104,
the hydrocarbon production system 12, or any other components
throughout the turbine-based service system 14 or the hydrocarbon
production system 12. For example, the sensor feedback 130 may
include temperature feedback, pressure feedback, flow rate
feedback, flame temperature feedback, combustion dynamics feedback,
intake oxidant composition feedback, intake fuel composition
feedback, exhaust composition feedback, the output level of
mechanical power 72, the output level of electrical power 74, the
output quantity of the exhaust gas 42, 60, the output quantity or
quality of the water 64, or any combination thereof. For example,
the sensor feedback 130 may include a composition of the exhaust
gas 42, 60 to facilitate stoichiometric combustion in the SEGR gas
turbine system 52. For example, the sensor feedback 130 may include
feedback from one or more intake oxidant sensors along an oxidant
supply path of the oxidant 68, one or more intake fuel sensors
along a fuel supply path of the fuel 70, and one or more exhaust
emissions sensors disposed along the exhaust recirculation path 110
and/or within the SEGR gas turbine system 52. The intake oxidant
sensors, intake fuel sensors, and exhaust emissions sensors may
include temperature sensors, pressure sensors, flow rate sensors,
and composition sensors. The emissions sensors may includes sensors
for nitrogen oxides (e.g., NO.sub.X sensors), carbon oxides (e.g.,
CO sensors and CO.sub.2 sensors), sulfur oxides (e.g., SO.sub.X
sensors), hydrogen (e.g., H.sub.2 sensors), oxygen (e.g., O.sub.2
sensors), unburnt hydrocarbons (e.g., HC sensors), or other
products of incomplete combustion, or any combination thereof.
[0054] Using this feedback 130, the control system 100 may adjust
(e.g., increase, decrease, or maintain) the intake flow of exhaust
gas 66, oxidant 68, and/or fuel 70 into the SEGR gas turbine system
52 (among other operational parameters) to maintain the equivalence
ratio within a suitable range, e.g., between approximately 0.95 to
approximately 1.05, between approximately 0.95 to approximately
1.0, between approximately 1.0 to approximately 1.05, or
substantially at 1.0. For example, the control system 100 may
analyze the feedback 130 to monitor the exhaust emissions (e.g.,
concentration levels of nitrogen oxides, carbon oxides such as CO
and CO.sub.2, sulfur oxides, hydrogen, oxygen, unburnt
hydrocarbons, and other products of incomplete combustion) and/or
determine the equivalence ratio, and then control one or more
components to adjust the exhaust emissions (e.g., concentration
levels in the exhaust gas 42) and/or the equivalence ratio. The
controlled components may include any of the components illustrated
and described with reference to the drawings, including but not
limited to, valves along the supply paths for the oxidant 68, the
fuel 70, and the exhaust gas 66; an oxidant compressor, a fuel
pump, or any components in the EG processing system 54; any
components of the SEGR gas turbine system 52, or any combination
thereof. The controlled components may adjust (e.g., increase,
decrease, or maintain) the flow rates, temperatures, pressures, or
percentages (e.g., equivalence ratio) of the oxidant 68, the fuel
70, and the exhaust gas 66 that combust within the SEGR gas turbine
system 52. The controlled components also may include one or more
gas treatment systems, such as catalyst units (e.g., oxidation
catalyst units), supplies for the catalyst units (e.g., oxidation
fuel, heat, electricity, etc.), gas purification and/or separation
units (e.g., solvent based separators, absorbers, flash tanks,
etc.), and filtration units. The gas treatment systems may help
reduce various exhaust emissions along the exhaust recirculation
path 110, a vent path (e.g., exhausted into the atmosphere), or an
extraction path to the EG supply system 78.
[0055] In certain embodiments, the control system 100 may analyze
the feedback 130 and control one or more components to maintain or
reduce emissions levels (e.g., concentration levels in the exhaust
gas 42, 60, 95) to a target range, such as less than approximately
10, 20, 30, 40, 50, 100, 200, 300, 400, 500, 1000, 2000, 3000,
4000, 5000, or 10000 parts per million by volume (ppmv). These
target ranges may be the same or different for each of the exhaust
emissions, e.g., concentration levels of nitrogen oxides, carbon
monoxide, sulfur oxides, hydrogen, oxygen, unburnt hydrocarbons,
and other products of incomplete combustion. For example, depending
on the equivalence ratio, the control system 100 may selectively
control exhaust emissions (e.g., concentration levels) of oxidant
(e.g., oxygen) within a target range of less than approximately 10,
20, 30, 40, 50, 60, 70, 80, 90, 100, 250, 500, 750, or 1000 ppmv;
carbon monoxide (CO) within a target range of less than
approximately 20, 50, 100, 200, 500, 1000, 2500, or 5000 ppmv; and
nitrogen oxides (NO.sub.X) within a target range of less than
approximately 50, 100, 200, 300, 400, or 500 ppmv. In certain
embodiments operating with a substantially stoichiometric
equivalence ratio, the control system 100 may selectively control
exhaust emissions (e.g., concentration levels) of oxidant (e.g.,
oxygen) within a target range of less than approximately 10, 20,
30, 40, 50, 60, 70, 80, 90, or 100 ppmv; and carbon monoxide (CO)
within a target range of less than approximately 500, 1000, 2000,
3000, 4000, or 5000 ppmv. In certain embodiments operating with a
fuel-lean equivalence ratio (e.g., between approximately 0.95 to
1.0), the control system 100 may selectively control exhaust
emissions (e.g., concentration levels) of oxidant (e.g., oxygen)
within a target range of less than approximately 500, 600, 700,
800, 900, 1000, 1100, 1200, 1300, 1400, or 1500 ppmv; carbon
monoxide (CO) within a target range of less than approximately 10,
20, 30, 40, 50, 60, 70, 80, 90, 100, 150, or 200 ppmv; and nitrogen
oxides (e.g., NO.sub.X) within a target range of less than
approximately 50, 100, 150, 200, 250, 300, 350, or 400 ppmv. The
foregoing target ranges are merely examples, and are not intended
to limit the scope of the disclosed embodiments.
[0056] The control system 100 also may be coupled to a local
interface 132 and a remote interface 134. For example, the local
interface 132 may include a computer workstation disposed on-site
at the turbine-based service system 14 and/or the hydrocarbon
production system 12. In contrast, the remote interface 134 may
include a computer workstation disposed off-site from the
turbine-based service system 14 and the hydrocarbon production
system 12, such as through an internet connection. These interfaces
132 and 134 facilitate monitoring and control of the turbine-based
service system 14, such as through one or more graphical displays
of sensor feedback 130, operational parameters, and so forth.
[0057] Again, as noted above, the controller 118 includes a variety
of controls 124, 126, and 128 to facilitate control of the
turbine-based service system 14. The steam turbine control 124 may
receive the sensor feedback 130 and output control commands to
facilitate operation of the steam turbine 104. For example, the
steam turbine control 124 may receive the sensor feedback 130 from
the HRSG 56, the machinery 106, temperature and pressure sensors
along a path of the steam 62, temperature and pressure sensors
along a path of the water 108, and various sensors indicative of
the mechanical power 72 and the electrical power 74. Likewise, the
SEGR gas turbine system control 126 may receive sensor feedback 130
from one or more sensors disposed along the SEGR gas turbine system
52, the machinery 106, the EG processing system 54, or any
combination thereof. For example, the sensor feedback 130 may be
obtained from temperature sensors, pressure sensors, clearance
sensors, vibration sensors, flame sensors, fuel composition
sensors, exhaust gas composition sensors, or any combination
thereof, disposed within or external to the SEGR gas turbine system
52. Finally, the machinery control 128 may receive sensor feedback
130 from various sensors associated with the mechanical power 72
and the electrical power 74, as well as sensors disposed within the
machinery 106. Each of these controls 124, 126, and 128 uses the
sensor feedback 130 to improve operation of the turbine-based
service system 14.
[0058] In the illustrated embodiment, the SEGR gas turbine system
control 126 may execute instructions to control the quantity and
quality of the exhaust gas 42, 60, 95 in the EG processing system
54, the EG supply system 78, the hydrocarbon production system 12,
and/or the other systems 84. For example, the SEGR gas turbine
system control 126 may maintain a level of oxidant (e.g., oxygen)
and/or unburnt fuel in the exhaust gas 60 below a threshold
suitable for use with the exhaust gas injection EOR system 112. In
certain embodiments, the threshold levels may be less than 1, 2, 3,
4, or 5 percent of oxidant (e.g., oxygen) and/or unburnt fuel by
volume of the exhaust gas 42, 60; or the threshold levels of
oxidant (e.g., oxygen) and/or unburnt fuel (and other exhaust
emissions) may be less than approximately 10, 20, 30, 40, 50, 60,
70, 80, 90, 100, 200, 300, 400, 500, 1000, 2000, 3000, 4000, or
5000 parts per million by volume (ppmv) in the exhaust gas 42, 60.
By further example, in order to achieve these low levels of oxidant
(e.g., oxygen) and/or unburnt fuel, the SEGR gas turbine system
control 126 may maintain an equivalence ratio for combustion in the
SEGR gas turbine system 52 between approximately 0.95 and
approximately 1.05. The SEGR gas turbine system control 126 also
may control the EG extraction system 80 and the EG treatment system
82 to maintain the temperature, pressure, flow rate, and gas
composition of the exhaust gas 42, 60, 95 within suitable ranges
for the exhaust gas injection EOR system 112, the pipeline 86, the
storage tank 88, and the carbon sequestration system 90. As
discussed above, the EG treatment system 82 may be controlled to
purify and/or separate the exhaust gas 42 into one or more gas
streams 95, such as the CO.sub.2 rich, N.sub.2 lean stream 96, the
intermediate concentration CO.sub.2, N.sub.2 stream 97, and the
CO.sub.2 lean, N.sub.2 rich stream 98. In addition to controls for
the exhaust gas 42, 60, and 95, the controls 124, 126, and 128 may
execute one or more instructions to maintain the mechanical power
72 within a suitable power range, or maintain the electrical power
74 within a suitable frequency and power range.
[0059] FIG. 3 is a diagram of embodiment of the system 10, further
illustrating details of the SEGR gas turbine system 52 for use with
the hydrocarbon production system 12 and/or other systems 84. In
the illustrated embodiment, the SEGR gas turbine system 52 includes
a gas turbine engine 150 coupled to the EG processing system 54.
The illustrated gas turbine engine 150 includes a compressor
section 152, a combustor section 154, and an expander section or
turbine section 156. The compressor section 152 includes one or
more exhaust gas compressors or compressor stages 158, such as 1 to
20 stages of rotary compressor blades disposed in a series
arrangement. Likewise, the combustor section 154 includes one or
more combustors 160, such as 1 to 20 combustors 160 distributed
circumferentially about a rotational axis 162 of the SEGR gas
turbine system 52. Furthermore, each combustor 160 may include one
or more fuel nozzles 164 configured to inject the exhaust gas 66,
the oxidant 68, and/or the fuel 70. For example, a head end portion
166 of each combustor 160 may house 1, 2, 3, 4, 5, 6, or more fuel
nozzles 164, which may inject streams or mixtures of the exhaust
gas 66, the oxidant 68, and/or the fuel 70 into a combustion
portion 168 (e.g., combustion chamber) of the combustor 160.
[0060] The fuel nozzles 164 may include any combination of premix
fuel nozzles 164 (e.g., configured to premix the oxidant 68 and
fuel 70 for generation of an oxidant/fuel premix flame) and/or
diffusion fuel nozzles 164 (e.g., configured to inject separate
flows of the oxidant 68 and fuel 70 for generation of an
oxidant/fuel diffusion flame). Embodiments of the premix fuel
nozzles 164 may include swirl vanes, mixing chambers, or other
features to internally mix the oxidant 68 and fuel 70 within the
nozzles 164. The premix fuel nozzles 164 also may receive at least
some partially mixed oxidant 68 and fuel 70. In certain
embodiments, each diffusion fuel nozzle 164 may isolate flows of
the oxidant 68 and the fuel 70 until the point of injection, while
also isolating flows of one or more diluents (e.g., the exhaust gas
66, steam, nitrogen, or another inert gas) until the point of
injection. In other embodiments, each diffusion fuel nozzle 164 may
isolate flows of the oxidant 68 and the fuel 70 until the point of
injection, while partially mixing one or more diluents (e.g., the
exhaust gas 66, steam, nitrogen, or another inert gas) with the
oxidant 68 and/or the fuel 70 prior to the point of injection. In
addition, one or more diluents (e.g., the exhaust gas 66, steam,
nitrogen, or another inert gas) may be injected into the combustor
(e.g., into the hot products of combustion) either at or downstream
from the combustion zone, thereby helping to reduce the temperature
of the hot products of combustion and reduce emissions of NO.sub.X
(e.g., NO and NO.sub.2). Regardless of the type of fuel nozzle 164,
the SEGR gas turbine system 52 may be controlled to provide
substantially stoichiometric combustion of the oxidant 68 and fuel
70.
[0061] In operation, as illustrated, the compressor section 152
receives and compresses the exhaust gas 66 from the EG processing
system 54, and outputs a compressed exhaust gas 170 to each of the
combustors 160 in the combustor section 154. Upon combustion of the
fuel 60, oxidant 68, and exhaust gas 170 within each combustor 160,
additional exhaust gas or products of combustion 172 (i.e.,
combustion gas) is routed into the turbine section 156. Similar to
the compressor section 152, the turbine section 156 includes one or
more turbines or turbine stages 174, which may include a series of
rotary turbine blades. These turbine blades are then driven by the
products of combustion 172 generated in the combustor section 154,
thereby driving rotation of a shaft 176 coupled to the machinery
106. Again, the machinery 106 may include a variety of equipment
coupled to either end of the SEGR gas turbine system 52, such as
machinery 106, 178 coupled to the turbine section 156 and/or
machinery 106, 180 coupled to the compressor section 152. In
certain embodiments, the machinery 106, 178, 180 may include one or
more electrical generators, oxidant compressors for the oxidant 68,
fuel pumps for the fuel 70, gear boxes, or additional drives (e.g.
steam turbine 104, electrical motor, etc.) coupled to the SEGR gas
turbine system 52. As illustrated, the turbine section 156 outputs
the exhaust gas 60 to recirculate along the exhaust recirculation
path 110 from an exhaust outlet 182 of the turbine section 156 to
an exhaust inlet 184 into the compressor section 152. Along the
exhaust recirculation path 110, the exhaust gas 60 passes through
the EG processing system 54 (e.g., the HRSG 56 and/or the EGR
system 58) as discussed in detail above.
[0062] Again, each combustor 160 in the combustor section 154
receives, mixes, and stoichiometrically combusts the compressed
exhaust gas 170, the oxidant 68, and the fuel 70 to produce the
additional exhaust gas or products of combustion 172 to drive the
turbine section 156. In certain embodiments, the oxidant 68 is
compressed by an oxidant compression system 186, such as a main air
compression (MAC) system. The oxidant compression system 186
includes an oxidant compressor 188 coupled to a drive 190. For
example, the drive 190 may include an electric motor, a combustion
engine, or any combination thereof. In certain embodiments, the
drive 190 may be a turbine engine, such as the gas turbine engine
150. Accordingly, the oxidant compression system 186 may be an
integral part of the machinery 106. In other words, the compressor
188 may be directly or indirectly driven by the mechanical power 72
supplied by the shaft 176 of the gas turbine engine 150. In such an
embodiment, the drive 190 may be excluded, because the compressor
188 relies on the power output from the turbine engine 150.
However, in the illustrated embodiment, the oxidant compression
system 186 is separate from the machinery 106. In either
embodiment, the compression system 186 compresses and supplies the
oxidant 68 to the fuel nozzles 164 and the combustors 160. As
discussed in further detail below, the oxidant 68 and the fuel 70
may be supplied to the gas turbine engine 150 at locations
specifically selected to facilitate isolation and extraction of the
compressed exhaust gas 170 without any oxidant 68 or fuel 70
degrading the quality of the exhaust gas 170.
[0063] The EG supply system 78, as illustrated in FIG. 3, is
disposed between the gas turbine engine 150 and the target systems
(e.g., the hydrocarbon production system 12 and the other systems
84). In particular, the EG supply system 78, e.g., the EG
extraction system (EGES) 80), may be coupled to the gas turbine
engine 150 at one or more extraction points 76 along the compressor
section 152, the combustor section 154, and/or the turbine section
156. For example, the extraction points 76 may be located between
adjacent compressor stages, such as 2, 3, 4, 5, 6, 7, 8, 9, or 10
interstage extraction points 76 between compressor stages. Each of
these interstage extraction points 76 provides a different
temperature and pressure of the extracted exhaust gas 42.
Similarly, the extraction points 76 may be located between adjacent
turbine stages, such as 2, 3, 4, 5, 6, 7, 8, 9, or 10 interstage
extraction points 76 between turbine stages. Each of these
interstage extraction points 76 provides a different temperature
and pressure of the extracted exhaust gas 42. By further example,
the extraction points 76 may be located at a multitude of locations
throughout the combustor section 154, which may provide different
temperatures, pressures, flow rates, and gas compositions. Each of
these extraction points 76 may include an EG extraction conduit,
one or more valves, sensors, and controls, which may be used to
selectively control the flow of the extracted exhaust gas 42 to the
EG supply system 78.
[0064] The extracted exhaust gas 42, which is distributed by the EG
supply system 78, has a controlled composition suitable for the
target systems (e.g., the hydrocarbon production system 12 and the
other systems 84). For example, at each of these extraction points
76, the exhaust gas 170 may be substantially isolated from
injection points (or flows) of the oxidant 68 and the fuel 70. In
other words, the EG supply system 78 may be specifically designed
to extract the exhaust gas 170 from the gas turbine engine 150
without any added oxidant 68 or fuel 70. Furthermore, in view of
the stoichiometric combustion in each of the combustors 160, the
extracted exhaust gas 42 may be substantially free of oxygen and
fuel. The EG supply system 78 may route the extracted exhaust gas
42 directly or indirectly to the hydrocarbon production system 12
and/or other systems 84 for use in various processes, such as
enhanced oil recovery, carbon sequestration, storage, or transport
to an offsite location. However, in certain embodiments, the EG
supply system 78 includes the EG treatment system (EGTS) 82 for
further treatment of the exhaust gas 42, prior to use with the
target systems. For example, the EG treatment system 82 may purify
and/or separate the exhaust gas 42 into one or more streams 95,
such as the CO.sub.2 rich, N.sub.2 lean stream 96, the intermediate
concentration CO.sub.2, N.sub.2 stream 97, and the CO.sub.2 lean,
N.sub.2 rich stream 98. These treated exhaust gas streams 95 may be
used individually, or in any combination, with the hydrocarbon
production system 12 and the other systems 84 (e.g., the pipeline
86, the storage tank 88, and the carbon sequestration system
90).
[0065] Similar to the exhaust gas treatments performed in the EG
supply system 78, the EG processing system 54 may include a
plurality of exhaust gas (EG) treatment components 192, such as
indicated by element numbers 194, 196, 198, 200, 202, 204, 206,
208, and 210. These EG treatment components 192 (e.g., 194 through
210) may be disposed along the exhaust recirculation path 110 in
one or more series arrangements, parallel arrangements, or any
combination of series and parallel arrangements. For example, the
EG treatment components 192 (e.g., 194 through 210) may include any
series and/or parallel arrangement, in any order, of: one or more
heat exchangers (e.g., heat recovery units such as heat recovery
steam generators, condensers, coolers, or heaters), catalyst
systems (e.g., oxidation catalyst systems), particulate and/or
water removal systems (e.g., inertial separators, coalescing
filters, water impermeable filters, and other filters), chemical
injection systems, solvent based treatment systems (e.g.,
absorbers, flash tanks, etc.), carbon capture systems, gas
separation systems, gas purification systems, and/or a solvent
based treatment system, or any combination thereof. In certain
embodiments, the catalyst systems may include an oxidation
catalyst, a carbon monoxide reduction catalyst, a nitrogen oxides
reduction catalyst, an aluminum oxide, a zirconium oxide, a
silicone oxide, a titanium oxide, a platinum oxide, a palladium
oxide, a cobalt oxide, or a mixed metal oxide, or a combination
thereof. The disclosed embodiments are intended to include any and
all permutations of the foregoing components 192 in series and
parallel arrangements. As illustrated below, TABLE 1 depicts some
non-limiting examples of arrangements of the components 192 along
the exhaust recirculation path 110.
TABLE-US-00001 TABLE 1 194 196 198 200 202 204 206 208 210 CU HRU
BB MRU PRU CU HRU HRU BB MRU PRU DIL CU HRSG HRSG BB MRU PRU OCU
HRU OCU HRU OCU BB MRU PRU HRU HRU BB MRU PRU CU CU HRSG HRSG BB
MRU PRU DIL OCU OCU OCU HRSG OCU HRSG OCU BB MRU PRU DIL OCU OCU
OCU HRSG HRSG BB COND INER WFIL CFIL DIL ST ST OCU OCU BB COND INER
FIL DIL HRSG HRSG ST ST OCU HRSG HRSG OCU BB MRU MRU PRU PRU ST ST
HE WFIL INER FIL COND CFIL CU HRU HRU HRU BB MRU PRU PRU DIL COND
COND COND HE INER FIL COND CFIL WFIL
[0066] As illustrated above in TABLE 1, a catalyst unit is
represented by CU, an oxidation catalyst unit is represented by
OCU, a booster blower is represented by BB, a heat exchanger is
represented by HX, a heat recovery unit is represented by HRU, a
heat recovery steam generator is represented by HRSG, a condenser
is represented by COND, a steam turbine is represented by ST, a
particulate removal unit is represented by PRU, a moisture removal
unit is represented by MRU, a filter is represented by FIL, a
coalescing filter is represented by CFIL, a water impermeable
filter is represented by WFIL, an inertial separator is represented
by INER, and a diluent supply system (e.g., steam, nitrogen, or
other inert gas) is represented by DIL. Although TABLE 1
illustrates the components 192 in sequence from the exhaust outlet
182 of the turbine section 156 toward the exhaust inlet 184 of the
compressor section 152, TABLE 1 is also intended to cover the
reverse sequence of the illustrated components 192. In TABLE 1, any
cell including two or more components is intended to cover an
integrated unit with the components, a parallel arrangement of the
components, or any combination thereof. Furthermore, in context of
TABLE 1, the HRU, the HRSG, and the COND are examples of the HE;
the HRSG is an example of the HRU; the COND, WFIL, and CFIL are
examples of the WRU; the INER, FIL, WFIL, and CFIL are examples of
the PRU; and the WFIL and CFIL are examples of the FIL. Again,
TABLE 1 is not intended to exclude any non-illustrated permutations
of the components 192. In certain embodiments, the illustrated
components 192 (e.g., 194 through 210) may be partially or
completed integrated within the HRSG 56, the EGR system 58, or any
combination thereof. These EG treatment components 192 may enable
feedback control of temperature, pressure, flow rate, and gas
composition, while also removing moisture and particulates from the
exhaust gas 60. Furthermore, the treated exhaust gas 60 may be
extracted at one or more extraction points 76 for use in the EG
supply system 78 and/or recirculated to the exhaust inlet 184 of
the compressor section 152.
[0067] As the treated, recirculated exhaust gas 66 passes through
the compressor section 152, the SEGR gas turbine system 52 may
bleed off a portion of the compressed exhaust gas along one or more
lines 212 (e.g., bleed conduits or bypass conduits). Each line 212
may route the exhaust gas into one or more heat exchangers 214
(e.g., cooling units), thereby cooling the exhaust gas for
recirculation back into the SEGR gas turbine system 52. For
example, after passing through the heat exchanger 214, a portion of
the cooled exhaust gas may be routed to the turbine section 156
along line 212 for cooling and/or sealing of the turbine casing,
turbine shrouds, bearings, and other components. In such an
embodiment, the SEGR gas turbine system 52 does not route any
oxidant 68 (or other potential contaminants) through the turbine
section 156 for cooling and/or sealing purposes, and thus any
leakage of the cooled exhaust gas will not contaminate the hot
products of combustion (e.g., working exhaust gas) flowing through
and driving the turbine stages of the turbine section 156. By
further example, after passing through the heat exchanger 214, a
portion of the cooled exhaust gas may be routed along line 216
(e.g., return conduit) to an upstream compressor stage of the
compressor section 152, thereby improving the efficiency of
compression by the compressor section 152. In such an embodiment,
the heat exchanger 214 may be configured as an interstage cooling
unit for the compressor section 152. In this manner, the cooled
exhaust gas helps to increase the operational efficiency of the
SEGR gas turbine system 52, while simultaneously helping to
maintain the purity of the exhaust gas (e.g., substantially free of
oxidant and fuel).
[0068] FIG. 4 is a flow chart of an embodiment of an operational
process 220 of the system 10 illustrated in FIGS. 1-3. In certain
embodiments, the process 220 may be a computer implemented process,
which accesses one or more instructions stored on the memory 122
and executes the instructions on the processor 120 of the
controller 118 shown in FIG. 2. For example, each step in the
process 220 may include instructions executable by the controller
118 of the control system 100 described with reference to FIG.
2.
[0069] The process 220 may begin by initiating a startup mode of
the SEGR gas turbine system 52 of FIGS. 1-3, as indicated by block
222. For example, the startup mode may involve a gradual ramp up of
the SEGR gas turbine system 52 to maintain thermal gradients,
vibration, and clearance (e.g., between rotating and stationary
parts) within acceptable thresholds. For example, during the
startup mode 222, the process 220 may begin to supply a compressed
oxidant 68 to the combustors 160 and the fuel nozzles 164 of the
combustor section 154, as indicated by block 224. In certain
embodiments, the compressed oxidant may include a compressed air,
oxygen, oxygen-enriched air, oxygen-reduced air, oxygen-nitrogen
mixtures, or any combination thereof. For example, the oxidant 68
may be compressed by the oxidant compression system 186 illustrated
in FIG. 3. The process 220 also may begin to supply fuel to the
combustors 160 and the fuel nozzles 164 during the startup mode
222, as indicated by block 226. During the startup mode 222, the
process 220 also may begin to supply exhaust gas (as available) to
the combustors 160 and the fuel nozzles 164, as indicated by block
228. For example, the fuel nozzles 164 may produce one or more
diffusion flames, premix flames, or a combination of diffusion and
premix flames. During the startup mode 222, the exhaust gas 60
being generated by the gas turbine engine 156 may be insufficient
or unstable in quantity and/or quality. Accordingly, during the
startup mode, the process 220 may supply the exhaust gas 66 from
one or more storage units (e.g., storage tank 88), the pipeline 86,
other SEGR gas turbine systems 52, or other exhaust gas
sources.
[0070] The process 220 may then combust a mixture of the compressed
oxidant, fuel, and exhaust gas in the combustors 160 to produce hot
combustion gas 172, as indicated by block 230. In particular, the
process 220 may be controlled by the control system 100 of FIG. 2
to facilitate stoichiometric combustion (e.g., stoichiometric
diffusion combustion, premix combustion, or both) of the mixture in
the combustors 160 of the combustor section 154. However, during
the startup mode 222, it may be particularly difficult to maintain
stoichiometric combustion of the mixture (and thus low levels of
oxidant and unburnt fuel may be present in the hot combustion gas
172). As a result, in the startup mode 222, the hot combustion gas
172 may have greater amounts of residual oxidant 68 and/or fuel 70
than during a steady state mode as discussed in further detail
below. For this reason, the process 220 may execute one or more
control instructions to reduce or eliminate the residual oxidant 68
and/or fuel 70 in the hot combustion gas 172 during the startup
mode.
[0071] The process 220 then drives the turbine section 156 with the
hot combustion gas 172, as indicated by block 232. For example, the
hot combustion gas 172 may drive one or more turbine stages 174
disposed within the turbine section 156. Downstream of the turbine
section 156, the process 220 may treat the exhaust gas 60 from the
final turbine stage 174, as indicated by block 234. For example,
the exhaust gas treatment 234 may include filtration, catalytic
reaction of any residual oxidant 68 and/or fuel 70, chemical
treatment, heat recovery with the HRSG 56, and so forth. The
process 220 may also recirculate at least some of the exhaust gas
60 back to the compressor section 152 of the SEGR gas turbine
system 52, as indicated by block 236. For example, the exhaust gas
recirculation 236 may involve passage through the exhaust
recirculation path 110 having the EG processing system 54 as
illustrated in FIGS. 1-3.
[0072] In turn, the recirculated exhaust gas 66 may be compressed
in the compressor section 152, as indicated by block 238. For
example, the SEGR gas turbine system 52 may sequentially compress
the recirculated exhaust gas 66 in one or more compressor stages
158 of the compressor section 152. Subsequently, the compressed
exhaust gas 170 may be supplied to the combustors 160 and fuel
nozzles 164, as indicated by block 228. Steps 230, 232, 234, 236,
and 238 may then repeat, until the process 220 eventually
transitions to a steady state mode, as indicated by block 240. Upon
the transition 240, the process 220 may continue to perform the
steps 224 through 238, but may also begin to extract the exhaust
gas 42 via the EG supply system 78, as indicated by block 242. For
example, the exhaust gas 42 may be extracted from one or more
extraction points 76 along the compressor section 152, the
combustor section 154, and the turbine section 156 as indicated in
FIG. 3. In turn, the process 220 may supply the extracted exhaust
gas 42 from the EG supply system 78 to the hydrocarbon production
system 12, as indicated by block 244. The hydrocarbon production
system 12 may then inject the exhaust gas 42 into the earth 32 for
enhanced oil recovery, as indicated by block 246. For example, the
extracted exhaust gas 42 may be used by the exhaust gas injection
EOR system 112 of the EOR system 18 illustrated in FIGS. 1-3.
[0073] FIG. 5 is a block diagram of an embodiment of the EG
processing system 54 as illustrated in FIGS. 1-3. In the
illustrated embodiment, the EG processing system 54 has the control
system 100 coupled to a plurality of gas treatment subsystems 300,
valves 302, and sensors (S) 304 distributed along the exhaust
recirculation path 110. For example, each subsystem 300 and its
components 192 may include one or more of the valves 302 and the
sensors 304 disposed internally within, upstream, and/or downstream
of the respective subsystem 300 or component 192. Although not
illustrated in FIG. 5, one or more valves 302 may be located at or
near the location of each sensor 304, thereby providing greater
flow control through the EG processing system 54. In operation, the
control system 100 may obtain sensor feedback 130 from the sensors
304 and provide control signals 306 to the valves 302, subsystems
300, and components 192 for control of the EG processing system 54.
The sensor feedback 130 also may include various sensor feedback
from the SEGR gas turbine system 52, the EG supply system 78, and
other components of the turbine-based service system 14.
[0074] Each of the gas treatment subsystems 300 may include one or
more components to control the temperature, pressure, gas
composition, moisture content, particulate content, or any
combination thereof. As illustrated in FIG. 5, the gas treatment
subsystems 300 include a catalyst and heat recovery (CHR) system
308, a moisture removal system (MRS) 310, and a particulate removal
system (PRS) 312. The gas treatment subsystems 300 also include one
or more booster blowers 314 to help increase the flow and pressure
of the exhaust gas 42 along the exhaust recirculation path 110.
Although the CHR 308, the booster blower 314, the MRS 310, and the
PRS 312 are arranged in series in the illustrated embodiment, other
embodiments may rearrange these components in other series and/or
parallel configurations.
[0075] The CHR system 308 includes one or more catalyst units 316
and heat exchangers (HX) 318 disposed in series, in parallel, or
integrated with one another. For example, the CHR system 308 may
include a series of catalysts units 316, such as catalyst units
320, 322, 324, 326, and 328. The CHR system 308 also may include a
series of heat exchangers 318, such as heat exchangers 330 and 332.
The catalyst units 316 may be the same or different from one
another. For example, one or more of the catalyst units 316 may
include an oxidation catalyst unit (OCU) 334, which uses an oxidant
fuel 336 to drive an oxidizing reaction to convert carbon monoxide
(CO) and unburnt hydrocarbons (HCs) into carbon dioxide (CO.sub.2)
and water vapor. One or more of the catalyst units 316 also may
drive a reduction reaction, which converts nitrogen oxides
(NO.sub.X) into carbon dioxide (CO.sub.2), nitrogen (N.sub.2), and
water. In the illustrated embodiment, the catalyst unit 320 is
disposed upstream of the heat exchanger 330, the catalyst unit 322
is integrated within the heat exchanger 330, the catalyst unit 324
is disposed between the heat exchanger 330 and the heat exchanger
332, the catalyst unit 326 is integrated within the heat exchanger
332, and the catalyst unit 328 is disposed downstream from the heat
exchanger 332. However, various embodiments of the CHR system 308
may exclude or include any one or more of the catalyst units 316,
or the catalyst units 316 may be disposed in other arrangements
within the CHR system 308.
[0076] The heat exchangers 318 are configured to transfer heat away
from the exhaust gas 42 into one or more gases, liquids, or other
fluids, such as water. In the illustrated embodiment, each heat
exchanger 318 includes a heat recovery unit (HRU) 338, which is
configured to recover heat from the exhaust gas 42 for use in one
or more other applications. For example, the illustrated heat
recovery units 338 each include a heat recovery steam generator
(HRSG) 340, which is configured to recover heat from the exhaust
gas 42 for the generation of steam 342. The steam 342 may be used
in a variety of processes within the EG processing system 54, the
EOR system 18, or elsewhere within the turbine-based service system
14. In the illustrated embodiment, each HRSG 340 supplies the steam
342 to one or more steam turbines (ST) 344, which may drive one or
more loads 346 to generate mechanical power 348 and/or electrical
power 350. For example, the loads 346 may include electrical
generators, which enable the generation of electrical power 350.
Although the CHR system 308 illustrates the catalyst units 316 and
the heat exchangers 318 in a series arrangement, other embodiments
of the CHR system 308 may arrange two or more of the catalyst units
316 and the heat exchangers 318 in a parallel arrangement. After
the exhaust gas 42 passes through the CHR system 308, the exhaust
gas 42 may then flow through one or more booster blowers 314 before
passing through the moisture removal system 310 and the particular
removal system 312.
[0077] The moisture removal system (MRS) 310 may include one or
more moisture removal units (MRU) 352, such as MRUs 354 and 356. In
the illustrated embodiment, the MRU 354 includes a heat exchanger
358, which may be configured to transfer heat away from the exhaust
gas 42 into another gas, liquid, or other fluid, thereby cooling
the exhaust gas 42 for moisture removal. For example, the heat
exchanger 358 may include or be configured as a condenser 360,
which functions to cool the exhaust gas 42 sufficiently to condense
moisture in the exhaust gas 42 and remove the condensate as water
362. However, the MRU 354 may include a variety of cooling units
(e.g., 2, 3, 4, or more condensers, chillers, etc.) to condense the
moisture from the exhaust 42, thereby producing the water 362. The
MRS 310 also may include other water removal technology, such as
filtration units. For example, the MRU 356 may include one or more
moisture removal separators or filters 364, such as a water gas
separator (WGS) 366, a water impermeable filter (WFIL) 368, and a
coalescing filter (CFIL) 370, which may capture and remove moisture
from the exhaust gas 42 to produce an output of water 372. Although
the MRS 310 illustrates the MRU 354 upstream from the MRU 356,
other embodiments of the MRS 310 may position the MRU 356 upstream
or parallel with the MRU 354. Furthermore, the MRS 310 may include
additional moisture removal filters 364, heat exchangers 358, or
any other moisture removal component. After the exhaust gas 42 is
treated by the MRS 310 to remove moisture, the exhaust gas 42 may
then pass through the particular removal system 312.
[0078] The particulate removal system (PRS) 312 may include one or
more particulate removal units (PRU) 374, which may be arranged in
series, in parallel, or any combination thereof. For example, the
PRS 312 may include a PRU 376 and a PRU 378 disposed in a series
arrangement. The PRU 376 may include an inertial separator 380, a
gravity separator 382, or any other type of separation unit, or any
combination thereof, thereby forcing a particulate 384 to separate
from a flow of the exhaust gas 42. For example, the inertial
separator 380 may include a centrifugal separator, which uses
centrifugal force to drive the particulate 384 out of the flow of
the exhaust gas 42. Similarly, the gravity separator 382 may use
the force of gravity to drive the particulate 384 out of the flow
of the exhaust gas 42. The PRU 378 may include one or more
particulate removal filters 386, such as a first stage filter 388
and a second stage filter 390. These staged filters 388 and 390 may
include progressively finer filter media, such as membrane filters.
However, the staged filters 388 and 390 may include water
impermeable filters (WFIL), coalescing filters (CFIL), membrane
filters, or any combination thereof. As the exhaust gas 42 passes
through the first and second stage filters 388 and 390, the filters
386 capture or remove a particulate 392 from the exhaust gas 42.
Although the illustrated PRS 312 has the PRU 376 upstream of the
PRU 378, other embodiments may position the PRU 378 upstream or
parallel with the PRU 376. After the exhaust gas 42 is treated by
the PRS 312, the exhaust gas 42 may then recirculate back into the
SEGR gas turbine system 52, as indicated by arrow 110.
[0079] Along the exhaust recirculation path 110, the CHR system
308, the MRS 310, the PRS 312, and the booster blower 314 may be
controlled by the control system 100 to adjust the temperature,
pressure, flow rate, moisture level, particulate level, and gas
composition of the exhaust gas 42 prior to entry back into the SEGR
gas turbine system 52. For example, the control system 100 may
receive the sensor feedback 130 from various sensors 304 disposed
along the exhaust recirculation path 110, thereby providing
feedback indicative of emissions (e.g. concentration levels) of
oxygen, carbon monoxide, hydrogen, nitrogen oxides (NO.sub.X),
unburnt hydrocarbons (HCs), sulfur oxides (SO.sub.X), moisture, or
any combination thereof. In response to the sensor feedback 130,
the control system 100 may adjust (e.g., increase, decrease, or
maintain) the pressure, temperature, or flow rate of the exhaust
gas 66, the oxidant 68, and the fuel 70 being delivered into the
SEGR gas turbine system 52 for combustion. For example, the control
system 100 may be responsive to the sensor feedback 130 to adjust
the valves 302 along the exhaust recirculation path 110, inlet
guide vanes within the compressor section 152 of the gas turbine
engine 150, a vent valve 394 leading to a vent system 396, or any
combination thereof, thereby adjusting the exhaust gas 42 flow into
the combustor section 154 of the gas turbine engine 150.
[0080] In the CHR system 308, the control system 100 may be
responsive to sensor feedback 130 to adjust the flow of oxidant
fuel 336 into each of the catalyst units 316, thereby increasing or
decreasing the oxidizing reaction within each catalyst unit 316 to
change the gas composition of the exhaust gas 42 that recirculates
back into the SEGR gas turbine system 52. For example, the control
system 100 may increase the flow of oxidant fuel 336 to increase
the oxidizing reaction within each UCU 334, thereby decreasing
levels of carbon monoxide (CO) and unburnt hydrocarbons (HCs) and
increasing levels of carbon dioxide (CO.sub.2). The control system
100 also may reduce the flow of oxidant fuel 336 into each of the
UCUs 334, thereby decreasing the levels of carbon dioxide
(CO.sub.2) and increasing levels of carbon monoxide (CO) and
unburnt hydrocarbons (HCs). The control system 100 also may
selectively increase or decrease the amount of exhaust gas flow
through each of the catalyst units 316, by pass one or more of the
catalyst units 316, or any combination thereof. The control system
100 also may selectively route the exhaust gas 42 through,
partially bypassing, or completely bypassing, one or more of the
heat exchangers 318, such as the heat recovery units 338. In this
manner, the control system 100 may increase or decrease the
temperature of the exhaust gas 42, while also increasing or
decreasing the amount of steam generation for driving the steam
turbines 344.
[0081] In the MRS 310 and the PRS 312, the control system 100 may
be responsive to the sensor feedback 130 to ensure sufficient
removal of moisture and particulate. For example, in response to
sensor feedback 130 indicative of moisture content, the control
system 100 may control the MRUs 352 within the MRS 310 to increase
or decrease the moisture removal from the exhaust gas 42. In
response to sensor feedback 130 indicative of particulate content,
the control system 100 may adjust the PRUs 374 within the PRS 312,
thereby increasing or decreasing the amount of particulate removal
from the exhaust gas 42. Each of these control actions by the
control system 100 may be based on feedback 130 from within the EG
processing system 54, the SEGR gas turbine system 52, or elsewhere
within the turbine-based service system 14. In certain embodiments,
the control system 100 is configured to maintain a temperature, a
pressure, and/or a flow rate of the exhaust gas 42 along the
exhaust recirculation path 110 within a respective target range
(e.g., a target temperature range, a target pressure range, and a
target flow rate range) within, upstream, or downstream of each
subsystem and/or component, such as the CHR system 308, the MRS
310, the PRS 312, or any of their components (e.g., catalyst units
316, heat exchangers 318, MRUs 352, PRUs 374, etc.). The control
system 100 may be configured to maintain the temperature, the
pressure, and/or the flow rate within such target ranges during
various controlled changes in the SEGR gas turbine system 52,
including changes in the flow rates of oxidant 68, fuel 70, and
diluent to the fuel nozzles 164 and combustors 160.
[0082] FIG. 6 is a diagram of an embodiment of a system 420 having
the EG supply system 78 extracting, treating, and delivering the
exhaust gas streams 95 to various target system 422. As discussed
above, the EG supply system 78 includes the exhaust extraction
system 80 and the EG treatment system 82. The exhaust extraction
system 80 receives the exhaust gas 42 from one or more extraction
points 76 along the SEGR gas turbine system 52, the EG processing
system 54, or any other location within the turbine-based service
system 14. The EG treatment system 82 then treats the extracted
exhaust gas 42 with a plurality of treatment subsystems 424, such
as a compression system 426, a moisture removal/dehydration system
428, a particulate removal/filtration system 430, a gas separation
system 432, and a gas purification system 434.
[0083] The illustrated treatment subsystems 424 may be disposed in
series, in parallel, or any combination thereof. The compression
system 426 may include one or more rotary compressors,
reciprocating compressors, or any combination thereof, in one or
more compression stages. The moisture removal/dehydration system
428 may include one or more heat exchangers, heat recovery units
such as heat recovery steam generators, condensers, water gas
separators such as centrifugal water gas separators, filters,
desiccants or other dehydration media, or any combination thereof.
The particulate removal/filtration system 430 may include one or
more inertial separators, gravity separators, filters, or any
combination thereof. For example, the filters may include membrane
filters, water impermeable filters, coalescing filters, or any
combination thereof. The gas separation system 432 may include one
or more solvent based separation systems, which may include one or
more absorbers, flash tanks, or any combination thereof. For
example, the gas separation system 432 may be configured to
separate carbon dioxide (CO.sub.2) and/or nitrogen (N.sub.2) from
the exhaust gas 42. By further example, the gas separation system
432 may include a CO.sub.2/N.sub.2 separator and/or a carbon
capture system. The gas purification system 432 also may include
one or more solvent based gas purifiers, and may further reduce
impurities within the separated gases (e.g., CO.sub.2 and/or
N.sub.2) from the gas separation system 432. For example, any
separated carbon dioxide (CO.sub.2) may be further purified by the
gas purification system 434, thereby increasing purity levels of
the separated carbon dioxide (CO.sub.2). Similarly, the gas
purification system 434 may further purify the separated nitrogen
(N.sub.2), thereby removing any impurities in the separated
nitrogen (N.sub.2). In certain embodiments, the separated carbon
dioxide and the separated nitrogen may have purity levels of at
least approximately 70, 80, 90, 95, 96, 97, 98, 99, or greater
percentage purity by volume. In certain embodiments, the gas
separation system 432 may generate the multiple exhaust gas streams
95, such as the first stream 96, the second stream 97, and the
third stream 98. For example, the first stream 96 may include a
CO.sub.2 rich stream 436, the second stream 97 may include an
intermediate concentration stream 438, and the third stream 98 may
include a CO.sub.2 lean stream 440.
[0084] One or more of these exhaust gas streams 95 may then pass to
one or more secondary gas treatment systems 442 and/or energy
recovery systems 444. For example, the first stream 96 may pass to
a secondary gas treatment system 446, the second stream 97 may pass
to a secondary gas treatment system 448, and the third stream 98
may pass to a secondary gas treatment system 450. Similarly, the
first stream 96 may pass to an energy recovery system 452, the
second stream 97 may pass to an energy recovery system 454, and the
third stream 98 may pass to an energy recovery system 456. Each of
the secondary gas treatment system 442 may include a compression
system 458, a moisture removal/dehydration system 460, or any other
suitable treatment components. Again, the compression system 458
may include one or more rotary compressors, reciprocating
compressors, or any combination thereof, disposed in a series or
parallel arrangement. The moisture removal/dehydration system 460
may include water gas separators, condensers, filters, or any
combination thereof, thereby removing any moisture remaining in the
streams 96, 97, or 98 after compression by the compression system
458. Again, each of the streams 96, 97, and 98 may pass through its
own dedicated secondary gas treatment system 442, or two or more of
these streams may share a common secondary gas treatment system
442. After this secondary treatment in the system 442, the treated
exhaust gas streams 96, 97, and 98 may then pass to one or more
target systems 422, such as the hydrocarbon production system 12,
the pipeline 86, the storage tank 88, and/or the carbon
sequestration system 90. In other words, any one or more of the
individual streams 96, 97, and 98 may be independently or
collectively used by one or more of the target systems 422.
[0085] In the energy recovery systems 444, each of the streams 96,
97, and 98 may enable energy recovery in one or more turbines or
expanders 462, which then drive one or more loads 464 to create
mechanical power 466 and/or electrical power 468. For example, the
load 464 may include one or more electrical generators to produce
the electrical power 468. Again, each one of the streams 96, 97,
and 98 may independently or collectively drive its own turbine or
expander 462 in its own dedicated energy recovery system 452, 454,
or 456. This recovered energy may be used to drive other equipment
throughout the turbine-based service system 14.
[0086] FIG. 7 is a diagram of an embodiment of the combustor
section 154 of the gas turbine engine 150. As illustrated, the
combustor section 154 has a casing 490 disposed about one or more
combustors 160, thereby defining a compressor discharge cavity 492
between the casing 490 and the combustor 160. Each combustor 160
includes the head end portion 166 and the combustion portion 168.
The combustion portion 168 may include a chamber 494, a first wall
or liner 496 disposed about the chamber 494, and a second wall or
flow sleeve 498 disposed at an offset around the first wall 496.
For example, the first and second walls 496 and 498 may be
generally coaxial with one another to define a hollow
circumferential space or flow passage 500 leading from the
combustion portion 168 to the head end portion 166. The second wall
or flow sleeve 498 may include a plurality of openings or
perforations 502, which enables the compressed exhaust gas 170 from
the compressor section 152 to enter into the flow passage 500. The
exhaust gas 170 then flows through the passage 500 along the liner
496 toward the head end portion 166 as indicated by arrows 504,
thereby cooling the liner 496 as the exhaust gas 170 flows toward
the head end portion 166 for delivery into the chamber 494 (e.g.
through one or more fuel nozzles 164).
[0087] In certain embodiments, the liner 496 also may include one
or more openings or perforations 506, thereby enabling injection of
a portion of the exhaust gas 170 directly into the chamber 494 as
indicated by arrows 508. For example, the exhaust gas injection 508
may serve as a diluent injection, which may be configured to
control the temperature, pressure, flow rate, gas composition
(e.g., emissions levels), or any combination thereof, within the
chamber 494. In particular, the exhaust gas injection 508 may help
to control the temperature within the chamber 494, such that
emissions of nitrogen oxides (NO.sub.X) may be substantially
reduced in the hot products of combustion. One or more additional
diluents, such as nitrogen, steam, other inert gases, or additional
exhaust gas, may be injected through one or more diluent injectors
510, as indicated by arrows 512. Together, the exhaust gas
injection 508 and diluent injection 512 may be controlled to adjust
the temperature, concentration levels of emissions, or other
characteristics of the hot combustion gases flowing through the
chamber 494.
[0088] In the head end portion 166, one or more fuel nozzles 164
may route the exhaust gas 170, the oxidant 68, the fuel 70, and one
or more diluents 514 (e.g., exhaust gas, steam, nitrogen, other
inert gases, or any combination thereof) into the chamber 494 for
combustion. For example, each combustor 160 may include 1, 2, 3, 4,
5, 6, 7, 8, or more fuel nozzles 164, each configured as a
diffusion fuel nozzle and/or a premix fuel nozzle. For example,
each fuel nozzle 164 may deliver the oxidant 68, the fuel 70, the
diluents 514, and/or the exhaust gas 170 as premixed or independent
streams into the chamber 494, thereby generating a flame 516. The
premixed streams of oxidant 68 and fuel 70 result in a premix
flame, whereas separate streams of oxidant 68 and fuel 70 result in
a diffusion flame.
[0089] The control system 100 is coupled to one or more fluid
supply systems 518, which control the pressure, temperature, flow
rate, and/or mixtures of the oxidant 68, the fuel 70, the diluents
514, and/or the exhaust gas 170. For example, the control system
100 may independently control flows of the oxidant 68, the fuel 70,
the diluents 514, and/or the exhaust gas 170 in order to control
the equivalence ratio, emissions levels (e.g. carbon monoxide,
nitrogen oxides, sulfur oxides, unburnt hydrocarbons, hydrogen,
and/or oxygen), power output, or any combination thereof. In
operation, the control system 100 may control the fluid supply
systems 518 to increase the flows of oxidant 68 and fuel 70 while
maintaining substantially stoichiometric combustion, or the control
system 100 may control the fluid supply systems 518 to decrease the
flows of oxidant 68 and fuel 70 while maintaining substantially
stoichiometric combustion. The control system 100 may perform each
of these increases or decreases in flow rates of the oxidant 68 and
the fuel 70 in incremental steps (e.g., 1, 2, 3, 4, 5, or more
steps), continuously, or any combination thereof. Furthermore, the
control system 100 may control the fluid supply systems 518 to
increase or decrease the flows of oxidant 68 and fuel 70 in order
to provide a fuel rich mixture, a fuel lean mixture, or any other
mixture of the oxidant 68 and the fuel 70, into the chamber 494,
thereby creating hot products of combustion or exhaust gas 520 with
a low oxygen concentration, a high oxygen concentration, or any
other suitable concentration of oxygen, unburnt hydrocarbons,
carbon monoxide, nitrogen oxides, sulfur oxides, and so forth.
While controlling the flows of oxidant 68 and fuel 70, the control
system 100 also may control the fluid supply system 518 to increase
or decrease flow of the diluents 514 (e.g., steam, exhaust gas,
nitrogen, or any other inert gas), thereby helping to control the
temperature, pressure, flow rate, and/or gas composition (e.g.,
emissions levels) of the hot products of combustion 520 passing
through the chamber 494 toward the turbine section 156.
[0090] The control system 100 also may control the EG supply system
78, including the EG extraction system 80 and the EG treatment
system 82. For example, the control system 100 may selectively open
or close one or more valves 522 disposed along extraction lines 524
between the combustor section 154 and the EG extraction system 80.
The control system 100 may selectively open or close these valves
522 to increase or decrease the flow of exhaust gas 42 to the EG
extraction system 80, while also selectively extracting the exhaust
gas from different locations resulting in different temperatures
and/or pressures of the exhaust gas being delivered to the EG
extraction system 80. The control system 100 also may control one
or more valves 526 disposed along lines 528 leading to a vent
system 530. For example, the control system 100 may selectively
open the valve 526 to vent a portion of the exhaust gas through the
vent system 530 into the atmosphere, thereby reducing the pressure
in the EG supply system 78.
[0091] As discussed above, each combustor 160 in the combustor
section 154 may include one or more fuel nozzles 164, which may be
configured as premix fuel nozzles and/or diffusion fuel nozzles.
For example, FIGS. 8, 9, and 10 illustrate embodiments of the fuel
nozzle 164 configured as a premix fuel nozzle 550 operable to
generate a premix flame 516, 552, whereas FIGS. 11-16 illustrate
embodiments of the fuel nozzle 164 configured as a diffusion fuel
nozzle 554 operable to generate a diffusion flame 516, 556. These
fuel nozzles 550 and 554 may be used alone or in any combination
with one another in each of the combustors 160, as discussed in
further detail below with reference to FIG. 17. For example, each
combustor 160 may include only premix fuel nozzles 550, only
diffusion fuel nozzles 554, or any combination of both premix fuel
nozzles 550 and diffusion fuel nozzles 554.
[0092] The premix fuel nozzles 550 may have a variety of
configurations to completely or partially premix the oxidant 68 and
the fuel 70, while also optionally premixing one or more diluents
514 such as the exhaust gas 170, steam, nitrogen, or any other
suitable inert gas. FIG. 8 is a diagram of an embodiment of the
premix fuel nozzle 550 having a mixing portion 558 coupled to an
injection portion 560. The mixing portion 558 includes at least one
mixing chamber 562 surrounded by at least one enclosure 564, while
the injection portion 560 includes at least one injection passage
566 surrounded by at least one conduit 568. For example, the
enclosure 564 of the mixing portion 558 may include one or more
conduits, injection holes, swirl vanes, flow interruptions, or
other structures to facilitate mixing between the oxidant 68 and
the fuel 70. The mixing portion 558 also may receive one or more
flows of the diluents 514, such as exhaust gas 170, steam,
nitrogen, or another inert gas, thereby mixing the diluent 514
along with the oxidant 68 and the fuel 70. Once the oxidant 68 and
the fuel 70 are sufficiently mixed within the mixing chamber 562,
the premix fuel nozzle 550 routes the fuel oxidant mixture through
the injection passage 566 to at least one injection outlet 570. The
exiting mixture of oxidant 68 and fuel 70 (and optionally one or
more diluents 514) may then ignite to create the premix flame 552.
In certain embodiments, the control system 100 may selectively
control the fluid supply system 518 to increase or decrease flows
of the oxidant 68 and the fuel 70 (and optionally one or more
diluents 514), thereby adjusting the equivalence ratio, emissions
levels generated by the premix flame 552, power output of the gas
turbine engine 150, or any combination thereof. In certain
embodiments, the illustrated premix fuel nozzle 550 may not premix
any diluent with the oxidant 68 and fuel 70, but rather one or more
diluents (e.g., exhaust gas, steam, nitrogen, or another inert gas)
may be provided after the point of combustion and/or downstream
from the premix flame 552. In this manner, the flows of oxidant 68
and fuel 70 may be independently controlled to provide a more
precise control of the fuel/oxidant ratio, thereby helping to
achieve stoichiometric combustion for improved flame stability
while also using the downstream diluents for control of the
temperature and emissions (e.g., NO.sub.X emissions).
[0093] FIG. 9 is a diagram of an embodiment of the premix fuel
nozzle 550 having a multi-stage configuration of the mixing portion
558. As illustrated, the mixing portion 558 includes first and
second mixing chambers 580 and 582, which are defined by first and
second enclosure portions 584 and 586 of the enclosure 564. The
first and second mixing chamber 580 and 582 are illustrated in a
series configuration, although other embodiments of the mixing
portion 558 may arrange the first and second mixing chambers 580
and 582 in a parallel configuration. The mixing portion 558 also
may include additional mixing chambers in combination with the
first and second mixing chambers 580 and 582. For example, the
mixing portion 558 may include 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, or
more mixing chambers in a series configuration, a parallel
configuration, or a combination thereof. Each mixing chamber 580
and 582 may include one or more mixing devices, such as swirl
vanes, flow interruptions, tortuous pathways, passages with
increasing and decreasing diameters, or any combination thereof. In
operation, the mixing portion 558 receives one or more flows of the
oxidant 68, the fuel 70, and one or more diluents 514 from the
fluid supply system 518. Again, the diluents 514 may include the
exhaust gas 170, steam, nitrogen, or one or more other inert gases.
Each mixing chamber 580 and 582 may receive and mix two or more
different fluids from the fluid supply system 518. For example, the
first mixing chamber 580 may receive and mix one or more streams of
the oxidant 68 and the fuel 70, while the second mixing chamber 582
may receive and mix one or more streams of the oxidant 68 and the
diluents 514 or the fuel 70 and the diluents 514. In other words,
the first and second mixing chambers 580 and 582 may receive and
mix two or more of the same fluid streams, or two or more different
fluid streams from the fluid supply system 518. In this manner, the
first and second mixing chambers 580 and 582 may sequentially mix
the various fluids from the fluid supply system 518, and then
direct the mixture into the injection passage 566 for delivery into
the chamber 494 of the combustor 160. As the mixture of oxidant 68,
fuel 70, and one or more diluents 514 flows through the injection
outlet 570 of the injection passage 566, the mixture ignites and
forms the premix flame 552. Again, the control system 100 may
selectively control the fluid supply system 518 to increase,
decrease, or maintain flows of the oxidant 68, the fuel 70, and one
or more diluents 514, thereby adjusting the equivalence ratio,
emissions levels, power output of the gas turbine engine 150, or
any combination thereof.
[0094] FIG. 10 is a diagram of an embodiment of the premix fuel
nozzle 550 having a staged mixing portion 558 with a parallel
mixing section 590 in series with a swirling section 592. The
parallel mixing section 590 includes the first and second mixing
chambers 580 and 582 as discussed above with reference to FIG. 9,
wherein the first and second mixing chambers 580 and 582 are
disposed parallel with one another upstream from the swirling
section 592. The swirling section 592 includes an inner conduit or
hub 594, an outer conduit 596 disposed about the inner conduit 594,
and a plurality of swirl vanes 598 extending radially between the
inner conduit 594 and the outer conduit 596. Each of the swirl
vanes 598 may be angled or curved to force the fluid flow to swirl
in a circumferential direction 600 about a longitudinal axis 602 of
the premix fuel nozzle 550. The inner conduit 594 defines an inner
passage 604, the outer conduit 596 defines an outer passage 606,
and each swirl vane 598 defines a radial passage 608. One or more
of the swirl vanes 598 also include a plurality of injection ports
610, which may be disposed directly on or upstream from a trailing
edge of each swirl vane 598.
[0095] In the illustrated embodiment, the fluid supply system 518
routes one or more flows of the oxidant 68 and the diluent 514 into
the first mixing chamber 580, while also delivering one or more
flows of the fuel 70 and the diluent 514 into the second mixing
chamber 582. The first mixing chamber 580 substantially mixes the
flows of oxidant 68 and diluent 514, and then routes the mixture
into the outer passage 606 between the inner and outer conduits 594
and 596 as indicated by arrows 612. The mixture 614 of oxidant 68
and diluent 514 then flows toward the plurality of swirl vanes 598
in the swirling section 592, where the swirl vanes 598 force the
mixture 614 to swirl about the axis 602 as indicated by arrow
600.
[0096] Simultaneously, the second mixing chamber 582 routes a
premixed flow of the fuel 70 and the diluent 514 into the inner
passage 604 defined by the inner conduit 594 as indicated by arrow
616. The mixture 618 of fuel 70 and diluent 514 then flows
lengthwise along the inner passage 604, and then turns radially
into the plurality of swirl vanes 598 as indicated by arrows 620.
Upon reaching the plurality of injection ports 610, the mixture 618
of fuel 70 and diluent 514 then passes through the injection ports
610 into the outer passage 606 as indicated by arrows 622. The two
mixtures (i.e., the premixed oxidant and diluent flow 614 and the
premixed fuel and diluent flow 622) then further mix within the
injection passage 566 as indicated by arrows 624. The mixture 624
of oxidant 68, fuel 70, and diluent 514 then exits the premix fuel
nozzle 550 through the injection outlet 570, and subsequently
ignites to form the premix flame 552. Again, the control system 100
may selectively control the fluid supply system 518 to
independently control flows of the oxidant 68, the fuel 70, and the
diluent 514, thereby increasing, decreasing, or maintaining the
equivalence ratio, emissions levels, power output, or any
combination thereof, of the gas turbine engine 150.
[0097] FIG. 11 is a diagram of an embodiment of the diffusion fuel
nozzle 554 having a plurality of independent passages 640 for
delivery of the oxidant 68 and the fuel 70 into the chamber 494 of
the combustor 160. The independent passages 640 may include a
plurality of concentric annular passages, a central passage
surrounded by a plurality of peripheral passages, or any
combination thereof. In the illustrated embodiment, the independent
passages 640 include one or more fuel passages 642 and one or more
oxidant passages 644. For example, the illustrated fuel passage 642
is a central fuel passage surrounded by an inner conduit 646, while
the one or more oxidant passages 644 are outer oxidant passages
disposed between the inner conduit 646 and an outer conduit or
structure 648. By further example, the oxidant passage 644 may
include a single annular oxidant passage or a plurality of discrete
oxidant passages disposed circumferentially about the fuel passage
642 between the inner and outer conduits 646 and 648. In these
embodiments, the oxidant and fuel passages 642 and 644 remain
isolated from one another along a full length of the diffusion fuel
nozzle 554. The inner and outer conduits 646 and 648 may function
as isolation walls, which maintain the separation between the
oxidant 68 and fuel 70. The fuel passage 642 terminates at a fuel
outlet 650 and the one or more oxidant passages 644 terminate at
one or more oxidant outlet 652. These fuel and oxidant outlets 650
and 652 may be disposed along a common plane or downstream end 654
of the diffusion fuel nozzle 554, thereby delaying mixing of the
oxidant 68 and the fuel 70 until after injection from the fuel
nozzle 554 into the chamber 494 of the combustor 160.
[0098] As the oxidant 68 and the fuel 70 mix or diffuse with one
another in the chamber 494, the diffusion flame 556 forms as
indicated by an outline or border 656. The outline 656 may
represent a diffusion wall or flame wall, where the oxidant 68 and
the fuel 70 mix and combust in a substantially stoichiometric
manner (e.g., substantially stoichiometric combustion). In other
words, the outline or border 656 may represent a stable flame wall
of the diffusion flame 556, wherein the equivalence ratio is
approximately 1.0 or between approximately 0.95 to 1.05. Similar to
the premix fuel nozzles 550 discussed above with reference to FIGS.
8-10, the diffusion fuel nozzle 554 may be controlled by the
control system 100 to vary the equivalence ratio, exhaust
emissions, power output of the gas turbine engine 150, or any
combination thereof. For example, the illustrated control system
100 selectively controls the fluid supply system 518 to increase,
decrease, or maintain flows of the oxidant 68 and the fuel 70 in
response to the sensor feedback 130.
[0099] FIG. 12 is a diagram of an embodiment of the diffusion fuel
nozzle 554 having a plurality of independent passages 670 with an
injection portion 672 and a mixing portion 674. The mixing portion
674 may include one or more inner mixing chambers 676 and one or
more outer mixing chambers 678. For example, the inner mixing
chambers 676 may be fuel/diluent mixing chambers, which are
configured to mix one or more streams of the fuel 70 and the
diluent 514. The outer mixing chambers 676 may include one or more
oxidant/diluent mixing chambers, which are configured to mix one or
more streams of the oxidant 68 and the diluent 514. Each of these
mixing chambers may include a surrounding structure, such as an
outer enclosure or conduit. For example, the mixing chambers 676
may be surrounded by an inner conduit or enclosure 680, while the
mixing chambers 678 may be surrounded by an outer conduit or
enclosure 682. In certain embodiments, the mixing chamber 678 may
be enclosed between the inner and outer conduits 680 and 682.
[0100] Similarly, the injection portion 672 includes one or more
fuel-diluent passages 684 and one or more oxidant-diluent passages
686. Each fuel-diluent passage 684 is fluidly coupled to one or
more of the mixing chambers 678, while each of the oxidant-diluent
passages 686 is fluidly coupled to one or more of the mixing
chambers 678. The fuel-diluent passage 684 may be surrounded by an
inner conduit 688, while the one or more oxidant-diluent passages
686 may be surrounded by an outer conduit 690. For example, the
illustrated fuel-diluent passage 684 may be a central fuel-diluent
passage 684, which is surrounded by one or more outer
oxidant-diluent passages 686. For example, the inner and outer
conduits 688 and 690 may be concentric annular conduits, which
define the passages 684 and 686 in a coaxial or concentric annular
arrangement. However, the fuel-diluent passage 684 may represent a
single central passage or a plurality of separate passages disposed
within the inner conduit 688. Likewise, the oxidant-diluent
passages 686 may represent a single annular passage or a plurality
of discrete passages spaced apart from one another
circumferentially around the fuel-diluent passage 684, while
remaining isolated from one another by the inner and outer conduits
688 and 690. In certain embodiments, the inner conduits 680 and 688
form a single continuous inner conduit, and the outer conduits 682
and 690 form a single continuous outer conduit.
[0101] In operation, the control system 100 selectively controls
the fluid supply system 518 to increase, decrease, or maintain
flows of the fuel 70 and the diluent 514 into the mixing chamber
676, which mixes the fuel 70 and diluent 514 before passing the
mixture into the fuel-diluent passage 684. Similarly, the control
system 100 selectively controls the fluid supply system 518 to
increase, decrease, or maintain flows of the oxidant 68 and the
diluent 514 into the one or more mixing chambers 678, which mix the
oxidant 68 and the diluent 514 before delivering the mixture into
the one or more oxidant-diluent passages 686. The diffusion fuel
nozzle 554 then separately flows the fuel-diluent mixture 698 along
the passage 684 to an outlet 692, while simultaneously flowing the
oxidant-diluent mixture 700 along the passages 686 to one or more
outlets 694. Similar to the embodiment of FIG. 11, the outlets 692
and 694 may be arranged along a common plane or downstream end 696
of the diffusion fuel nozzle 554, thereby maintaining isolation
between the oxidant-diluent mixture 700 in the passage 686 and the
fuel-diluent mixture 698 in the passage 684. This isolation delays
mixing between the oxidant 68 and the fuel 70 until downstream of
the common plane 696.
[0102] As the fuel-diluent mixture 698 and the oxidant-diluent
mixture 700 flow from the diffusion fuel nozzle 554 into the
chamber 494 of the combustor 160, the mixtures 698 and 700
generally diffuse with one another and combust along an outline or
border 702, which may define a diffusion wall or flame wall of the
diffusion flame 556. Again, the control system 100 may selectively
control the fluid supply system 518 to independently control flows
of the oxidant 68, the fuel 70, and the diluent 514 to each of the
mixing chambers 676 and 678, thereby controlling mixing within each
of the mixing chambers 676 and 678 while also controlling the
diffusion and combustion within the chamber 494 of the combustor
160. For example, the control system 100 may selectively control
the fluid supply system 518 to adjust the ratio of the oxidant 68
relative to the fuel 70, the ratio of the diluent 514 relative to
the combined flow of the oxidant 68 and the fuel 70, the ratio of
the oxidant 68 relative to the diluent 514 in each of the one or
more mixing chambers 678 and corresponding passages 686, and the
ratio of the fuel 70 relative to the diluent 514 in each of the one
or more mixing chambers 676 and corresponding passages 684. Thus,
the control system 100 may adjust each of these ratios, flow rates,
temperatures, and fluid compositions (e.g., compositions of the
oxidant 68, the fuel 70, and the diluent 514) to adjust the
equivalence ratio, the exhaust emissions, and the power output of
the gas turbine engine 150.
[0103] FIG. 13 is a diagram of an embodiment of the diffusion fuel
nozzle 554, illustrating a plurality of independent passages 720.
The illustrated passages 640 include a fluid A passage 722, one or
more fluid B passages 724, and one or more fluid C passages 726.
The fluid A passage 722 may be separated or isolated from the one
or more fluid B passages 724 by a conduit or structure 728, the one
or more fluid B passages 724 may be separated from the one or more
fluid C passages 726 by a conduit or structure 730, and the one or
more fluid C passages 726 may be surrounded or supported by an
outer conduit or structure 732.
[0104] For example, as illustrated in FIG. 14, the fluid passages
722, 724, and 726 may be disposed in a concentric arrangement,
wherein the conduit 728 surrounds the fluid A passage 722 as a
central fluid passage, the fluid B passage 724 is disposed between
the conduits 728 and 730, and fluid C passage 726 is disposed
between the conduits 730 and 732. Again, the conduits 728, 730, and
732 may be disposed in a concentric arrangement, such that the
fluid B passage 724 and fluid C passage 726 each represent a
continuous annular passage.
[0105] However, the diffusion fuel nozzle 554 may arrange the
passages 722, 724, and 726 in other arrangements, such as discrete
passages as illustrated in FIG. 15. In the embodiment of FIG. 15,
the fluid A passage 722 represents a central fluid passage, while
the fluid B passages 724 and the fluid C passages 726 represent a
plurality of discrete passages that are spaced apart from one
another within the fuel nozzle 554. For example, the fluid B
passages 724 may include 2, 3, 4, 5, 6, 7, 8, or more discrete
fluid passages that are spaced apart from one another
circumferentially about the central fluid A passage 722. Likewise,
the fluid C passages 726 may include a plurality of discrete
passages that are spaced apart from one another circumferentially
about the fluid B passages 724. For example, the fluid B passages
724 may be arranged in a first ring or circular pattern of the
passages 724, while the fluid C passages 726 may be arranged in a
second ring or circular pattern of the passages 726.
[0106] In either of these configurations, the diffusion fuel nozzle
554 of FIG. 13 is configured to separately flow a fluid A 734
through the fluid A passage 722, a fluid B 736 through the one or
more fluid B passages 724, and a fluid C 738 through the one or
more fluid C passages 726. Each of these fluids 734, 736, and 738
may include one or more fluids, such as the oxidant 68, the fuel
70, and the diluents 514. However, the fluids 734, 736, and 738 may
not mix any of the oxidant 68 and the fuel 70 within the diffusion
fuel nozzle 554, thereby delaying mixing between the oxidant 68 and
the fuel 70 until the fluids eject from openings 740, 742, and 744
into the chamber 494 of the combustor 160. Again, these openings
740, 742, and 744 may be disposed along a common plane or
downstream end 746 of the diffusion fuel nozzle 554. The various
fluids then mix and combust to form the diffusion flame 556, as
discussed above. The following TABLE 2 illustrates some possible
non-limiting examples of fluids A, B, and C, which may be used with
the diffusion fuel nozzle 554 of FIGS. 13-15.
TABLE-US-00002 TABLE 2 FLUID A (722) FLUID B (724) FLUID C (726)
FUEL OXIDANT DILUENT FUEL DILUENT OXIDANT FUEL OXIDANT + DILUENT
OXIDANT FUEL OXIDANT OXIDANT + DILUENT FUEL + DILUENT FUEL OXIDANT
FUEL FUEL + DILUENT OXIDANT FUEL + DILUENT OXIDANT + DILUENT
OXIDANT FUEL + DILUENT OXIDANT OXIDANT + DILUENT FUEL OXIDANT +
DILUENT OXIDANT + DILUENT
[0107] As indicated above, the diffusion fuel nozzle 554 may flow a
variety of combinations of fluids (e.g., oxidant 68, fuel 70, and
diluent 514) through the passages 722, 724, and 726 for generation
of a diffusion flame 556. Again, the oxidant 68 may include oxygen,
ambient air, oxygen enriched air, oxygen reduced air, mixtures of
nitrogen and oxygen, or any combination thereof. The fuel 70 may
include liquid fuel and/or gas fuel, such as natural gas, syngas,
or any other fuel described herein. The diluent 514 may include the
exhaust gas 170, steam, nitrogen, or another inert gas, or any
combination thereof. Although TABLE 2 depicts some possible
examples of the fluids, any combination of fluids may be used with
the diffusion fuel nozzle 554 of FIGS. 13-15. In addition, although
the depicted embodiment does not mix any fuel 70 with oxidant 68
within the diffusion fuel nozzle 554, other embodiments may mix a
small amount (e.g., less than 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10
percent by volume) of oxidant 68 with fuel 70 or a small amount
(e.g., less than 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10 percent by
volume) of fuel 70 with oxidant 68.
[0108] FIG. 16 is a diagram of an embodiment of the combustor
section 154 having one of the diffusion fuel nozzles 554 disposed
within the combustor 160. Similar to the diffusion fuel nozzle 554
illustrated in FIGS. 13-15, the diffusion fuel nozzle 554 of FIG.
16 includes the fluid A passage 724 surrounded by the conduit 728,
the fluid B passage 724 surrounded by the conduit 730, the fluid C
passage 726 surrounded by the conduit 732, and a fluid D passage
760 surrounded by an outer conduit or structure 762. The fluid D
passage 760 is configured to receive a fluid D 764 from the fluid
supply system 518, and route the fluid D 764 into the chamber 494
through one or more outlets 766. The passages 722, 724, 726, and
760 may have the respective outlets 740, 742, 744, and 766 disposed
along the common plane or downstream end 746 of the diffusion fuel
nozzle 554, thereby isolating the flows of the fluids 734, 736,
738, and 764 until the fluids reach the chamber 494. In this
manner, the diffusion fuel nozzle 554 facilitates the formation of
the diffusion flame 556. Each of the fluids 734, 736, 738, and 764
may include the oxidant 68, the fuel 70, and one or more diluents
514, such as the exhaust gas 170, steam, nitrogen, and/or one or
more other inert gases. However, the fluid passages 722, 724, 726,
and 760 may not mix any of the oxidant 68 and the fuel 70 within
the diffusion fuel nozzle 554, thereby facilitating isolation of
the oxidant 68 and fuel 70 until the fluids reach the chamber 494.
The oxidant 68 and the fuel 70 may flow through each of the
independent fluid passages 722, 724, 726, and 760, either
separately or partially premixed with one or more of the diluents
514. Similar to the previous embodiments, the control system 100
may selectively control the fluid supply system 518 to increase,
decrease, or maintain the flows of each fluid 734, 736, 738, and
764, thereby adjusting the fluid flow ratios among the fluids, the
equivalence ratio, the emissions level, the power output of the gas
turbine engine 150, or any combination thereof.
[0109] The illustrated combustor 160 of FIG. 16 also includes a
diluent injection system 770 disposed along the combustion portion
168 of the combustor 160, such that one or more diluents (e.g.,
exhaust gas 170, steam, nitrogen, or other inert gases) may be
injected into the chamber 494 to control the temperature, pressure,
flow rate, gas composition (e.g., emissions levels), or any
combination thereof, of the hot products of combustion 772 formed
by the diffusion flame 556. For example, the diluent injection
system 770 may include the openings of perforations 506 disposed in
the first wall or liner 496, and a plurality of the diluent
injectors 510 extending through the first and second walls 496 and
498 to the chamber 494 of the combustor 160. In operation, the
openings or perforations 506 may be configured to inject a fluid E
774, such as the exhaust gas 170, as indicated by arrows 508. The
diluent injectors 510 may be configured to inject a fluid F 776
and/or a fluid G 778 into the chamber 494, as indicated by arrows
512. For example, the fluid F 776 and the fluid G 778 may include
additional exhaust gas 170, steam, nitrogen, one or more other
inert gases, or any combination thereof. These injected diluents
508 and 512 may be configured to control the temperature, pressure,
flow rate, gas composition (e.g., emissions levels), or any
combination thereof, of the hot products of combustion 772
resulting from the diffusion flame 556. In certain embodiments, the
control system 100 may selectively control the fluid supply systems
518 to increase, decrease, or maintain flows of the various fluids
734, 736, 738, 764, 774, 776, and 778, thereby controlling the
ratio of the oxidant 68 to fuel 70, the ratio of one or more
diluents 514 relative to the oxidant 68 and the fuel 70, or any
combination thereof. In turn, these control adjustments of the
fluids may alter the equivalence ratio, emissions levels, and power
output of the gas turbine engine 150. The following TABLE 3
illustrates some possible non-limiting examples of fluids A, B, C,
D, E, F, and G, which may be used with the diffusion fuel nozzle
554 and combustor 160 of FIG. 16.
TABLE-US-00003 TABLE 3 FLUID A FLUID B FLUID C FLUID D FLUID E
FLUID F FLUID G (722) (724) (726) (764) (774) (776) (778) FUEL FUEL
OXIDANT OXIDANT DILUENT DILUENT DILUENT FUEL OXIDANT FUEL OXIDANT
DILUENT DILUENT DILUENT OXIDANT FUEL OXIDANT FUEL DILUENT DILUENT
DILUENT FUEL + FUEL + OXIDANT + OXIDANT + DILUENT DILUENT DILUENT
DILUENT DILUENT DILUENT DILUENT FUEL + OXIDANT + FUEL + OXIDANT +
DILUENT DILUENT DILUENT DILUENT DILUENT DILUENT DILUENT OXIDANT +
FUEL + OXIDANT + FUEL + DILUENT DILUENT DILUENT DILUENT DILUENT
DILUENT DILUENT DILUENT FUEL FUEL + OXIDANT + DILUENT OXIDANT
DILUENT DILUENT DILUENT DILUENT OXIDANT OXIDANT + FUEL + DILUENT
FUEL DILUENT DILUENT DILUENT FUEL OXIDANT FUEL OXIDANT DILUENT FUEL
DILUENT
[0110] As indicated above, the diffusion fuel nozzle 554 and
combustor 160 may flow a variety of combinations of fluids (e.g.,
oxidant 68, fuel 70, and diluent 514) through the passages 722,
724, 726, and 760, openings 506, and diluent injectors 510 for
generation of a diffusion flame 556. Again, the oxidant 68 may
include oxygen, ambient air, oxygen enriched air, oxygen reduced
air, mixtures of nitrogen and oxygen, or any combination thereof.
The fuel 70 may include liquid fuel and/or gas fuel, such as
natural gas, syngas, or any other fuel described herein. The
diluent 514 may include the exhaust gas 170, steam, nitrogen, or
another inert gas, or any combination thereof. Although TABLE 3
depicts some possible examples of the fluids, any combination of
fluids may be used with the diffusion fuel nozzle 554 and combustor
160 of FIG. 16. In addition, although the depicted embodiment does
not mix any fuel 70 with oxidant 68 within the diffusion fuel
nozzle 554, other embodiments may mix a small amount (e.g., less
than 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10 percent by volume) of oxidant
68 with fuel 70 or a small amount (e.g., less than 1, 2, 3, 4, 5,
6, 7, 8, 9, or 10 percent by volume) of fuel 70 with oxidant
68.
[0111] FIG. 17 is a schematic cross-section of the combustor 160
taken along line 17-17 of FIG. 7, further illustrating a
multi-nozzle arrangement of the fuel nozzles 164 and a
multi-injector arrangement of the diluent injectors 510. The
illustrated fuel nozzles 164 include a fuel nozzle A 790, a fuel
nozzle B 792, a fuel nozzle C 794, a fuel nozzle D 796, a fuel
nozzle E 798, a fuel nozzle F 800, and a fuel nozzle G 802. In the
illustrated embodiment, the nozzle 790 is a central fuel nozzle,
which is surrounded by the remaining fuel nozzles 792, 794, 796,
798, 800 and 802 as outer or peripheral fuel nozzles. Although the
illustrated embodiment includes a single central fuel nozzle 164
and six outer fuel nozzles 164, other embodiments may include any
number of central and outer fuel nozzles. The illustrated fuel
nozzles 164 may include one or more of the premix fuel nozzles 550
and/or the diffusion fuel nozzles 554 shown and described with
reference to FIGS. 8-16. For example, all of the fuel nozzles 164
may be configured as premix fuel nozzles 550, all of the fuel
nozzles 164 may be configured as diffusion fuel nozzles 554, or the
fuel nozzles 164 may include one or more of both the premix fuel
nozzles 550 and the diffusion fuel nozzles 554. The fluid flows to
the fuel nozzles 164 may be independently controlled for each fuel
nozzle 164, or the fluid flows may be controlled in groups of fuel
nozzles 164. For example, the central fuel nozzle 790 may be
controlled independently from one or more groups of the outer fuel
nozzles 792, 794, 796, 798, 800, and 802. By further example, one
or more premix fuel nozzles 550 may be controlled independently
from one or more diffusion fuel nozzles 554. These different
control schemes may facilitate different operations modes, which
may be useful in providing stoichiometric combustion and reducing
emissions in the exhaust gas 42.
[0112] As further illustrated in FIG. 17, the fuel nozzles 164 and
diluent injectors 510 may be coupled to the fluid supply system 518
through a plurality of fluid supply circuits 810, such as one or
more diluent supply circuits 812 and one or more fuel nozzle supply
circuits 814. For example, the diluent supply circuits 812 may
include 1, 2, 3, 4, 5, 6, 7, 8, or more independent diluent supply
circuits 812, thereby enabling a variety of diluent injection modes
for the diluent injectors 510. Similarly, the fuel nozzle supply
circuits 814 may include 1, 2, 3, 4, 5, 6, 7, 8, or more
independent fuel nozzle supply circuits 814, thereby enabling a
variety of fluid supply modes for the fuel nozzles 164. For
example, the fuel nozzle supply circuits 814 may include a first
nozzle circuit 816, a second nozzle circuit 818, and a third nozzle
circuit 820. Each of these fuel nozzle supply circuits 814 (e.g.,
816, 818, and 820) may include one or more fuel lines, oxidant
lines, and/or diluent lines (e.g., exhaust lines, steam lines,
nitrogen lines, and/or other inert gas lines), which are fluidly
coupled to at least one fuel nozzle 164. In the illustrated
embodiment, the first nozzle circuit 816 is coupled to a first set
of fuel nozzles 164 (e.g., the central fuel nozzle 790), the second
nozzle circuit 818 is coupled to a second set of fuel nozzles 164
(e.g., outer fuel nozzles 794, 798, and 802), and the third nozzle
circuit 820 is coupled to a third set of fuel nozzles 164 (e.g.,
outer fuel nozzles 792, 796, and 800). In some embodiments, each
set of fuel nozzles 164 coupled to one of the nozzle supply
circuits 814 may be entirely diffusion fuel nozzles, entirely
premix fuel nozzles, or any combination of diffusion fuel nozzles
and premix fuel nozzles. However, any number or configuration of
fuel nozzles 164 may be coupled to each fuel nozzle supply circuit
814, and any number of nozzle supply circuits 814 may be coupled to
the fuel nozzles 164. Again, the fuel nozzle supply circuits 814
are coupled to the fluid supply system 518, which may include
valves, flow regulators, and other flow controls to control the
flow rate and pressure of the flows to the fuel nozzles 164.
[0113] In turn, the fluid supply system 518 is coupled to the
control system 100, which may use the controller 118 to receive the
sensor feedback 130 and provide controls signals 306 to the fluid
supply system 518 to control operation of the circuits 812 and 814.
In the illustrated embodiment, the controller 118 of the system 100
may store and execute (e.g., computer instructions or code relating
to) a stoichiometric control mode 822 and a non-stoichiometric
control mode 824, which may further include a fuel-lean control
mode 826 and a fuel-rich control mode 828. The controller 118 of
the system 100 also may store and execute (e.g., computer
instructions or code relating to) a fluid supply control 830,
including a first fluid circuit control 832, a second fluid circuit
control 834, and a third fluid circuit control 836. For example,
the first fluid circuit control 832 may be configured to control
various flow rates (e.g., oxidant 68, fuel 70, and/or diluent 514)
to the first nozzle circuit 816, the second fluid circuit control
834 may be configured to control various flow rates (e.g., oxidant
68, fuel 70, and/or diluent 514) to the second nozzle circuit 818,
and the third fluid circuit control 836 may be configured to
control various flow rates (e.g., oxidant 68, fuel 70, and/or
diluent 514) to the third nozzle circuit 820.
[0114] In certain embodiments, the stoichiometric control mode 822
is configured to change the flow rates of at least one fuel 70 and
at least one oxidant 68 and provide a substantially stoichiometric
ratio of the fuel 70 with the oxidant 68, whereas the
non-stoichiometric control mode 824 is configured to change the
flow rates and provide a non-stoichiometric ratio of the fuel 70
with the oxidant 68. For example, the stoichiometric control mode
822 may be configured to provide the substantially stoichiometric
ratio with an equivalence ratio of approximately 1.0, or between
approximately 0.95 and approximately 1.05. In contrast, the
non-stoichiometric control mode 824 may be configured to provide
the non-stoichiometric ratio with an equivalence ratio of less than
approximately 0.95 or greater than approximately 1.05. In some
embodiments, the control system 100 may be configured to change the
flow rates from a first set of flow rates to a second set of flow
rates, wherein the first and second flow rates are different from
one another (e.g., greater or lesser than one another). The
controlled change in flow rates may also involve a transition
between the stoichiometric control mode 822 and the
non-stoichiometric control mode 824, or the controlled change in
flow rates may involve maintaining the substantially stoichiometric
ratio. The controlled change in flow rates also may involve a
change in power output (or load) of the SEGR gas turbine system 52
from a first power output (or first load) to a second power output
(or second load), wherein the first and second power outputs (e.g.,
loads) are different from one another (e.g., lesser or greater than
one another). For example, the controlled change in power outputs
may involve a controlled change in turbine load, e.g., a reduction
from a rated or normal load (e.g., 100 percent) to a partial load
(e.g., 50 percent). The controlled change in flow rates also may
involve maintaining emissions in the exhaust gas within one or more
target emissions ranges, wherein the emissions may include carbon
monoxide, oxygen, nitrogen oxides, sulfur oxides, unburnt
hydrocarbons, hydrogen, or any combination thereof. In certain
embodiments, the one or more target emissions ranges may include an
oxygen range of less than approximately 50 parts per million by
volume (ppmv) and/or a carbon monoxide range of less than
approximately 5000 ppmv. In other embodiments, the one or more
target emissions ranges comprise an oxygen range of less than
approximately 10 ppmv and/or a carbon monoxide range of less than
approximately 1000 ppmv.
[0115] In some embodiments, the control system 100 in the
stoichiometric control mode 822 is configured to maintain the
substantially stoichiometric ratio while progressively reducing the
flow rates (e.g., oxidant 68 and fuel 70) among a plurality of sets
of flow rates, progressively reducing a power output (e.g., load)
of the SEGR gas turbine system 52 among a plurality of power
outputs (e.g., full load, first partial load, second partial load,
etc.), and maintaining emissions in the exhaust gas within one or
more target emissions ranges. The control system 100 also may be
configured to transition from the stoichiometric control mode 822
to the non-stoichiometric control mode 824 after progressively
reducing the flow rates, progressively reducing the power output,
and maintaining emissions. After the transition from the
stoichiometric control mode 822 to the non-stoichiometric control
mode 824, the control system 100 also may be configured to operate
in a fuel-rich control mode or a fuel-lean control mode of the
non-stoichiometric control mode 824. The control system 100 also
may be configured to maintain emissions in the exhaust gas within a
first set of target emissions ranges (e.g., while operating in the
stoichiometric control mode 822) and a second set of target
emissions ranges (e.g., while operating in the non-stoichiometric
control mode 824), wherein the first and second sets of target
emissions ranges are different from one another. Although the
foregoing examples provide a number of control scenarios for the
SEGR gas turbine engine 52, it should be understood that any number
of control scenarios may be executed by the control system 100
using diffusion fuel nozzles, premix fuel nozzles, or any
combination thereof.
[0116] FIG. 18 is a graph of exhaust gas recirculation (EGR) flow
rate and gas turbine load 840 versus fuel/oxidant ratio 842 for the
SEGR gas turbine system 52, illustrating a diffusion flame
operability curve 844 and a premix flame operability curve 846. The
EGR flow rate through the SEGR gas turbine system 52 is generally
proportionally to the load on the gas turbine engine 150, and thus
the Y-axis 840 generally indicates both EGR flow rate and gas
turbine load. In general, the areas above and to the left of each
curve 844 and 846 represent unstable regions for each flame
configuration of the SEGR gas turbine system 52. It is noteworthy
that the diffusion flame operability curve 844 substantially
exceeds the premix flame operability curve 846, indicating a
substantially greater EGR flow rate and load range for the SEGR gas
turbine system 52 operating with diffusion combustion. As
illustrated in FIG. 18, the diffusion flame operability curve 844
may correspond to a combustor 160 equipped with a diffusion fuel
nozzle 554, wherein exhaust gas (e.g., diluent) is injected
downstream from the diffusion fuel nozzle 554 after the point of
combustion and/or downstream from the diffusion flame 556 generated
by the nozzle 554. One example of such a diffusion combustion
configuration is illustrated in FIG. 16. In contrast, the premix
flame operability curve 846 may correspond to a combustor 160
equipped with a premix fuel nozzle 550, wherein the oxidant 68, the
fuel 70, and the diluent 514 (e.g., exhaust gas) are premixed prior
to the point of combustion (i.e., upstream from the premix flame
552). Again, the diffusion flame operability curves 844 indicates
much greater EGR flow rates through the SEGR gas turbine system 52,
which also means a greater production of CO.sub.2 for use in the
target systems 422. The SEGR gas turbine system 52 operating with
the foregoing diffusion combustion configuration also may have
substantially reduced emissions of oxygen and carbon monoxide.
These emissions reductions may be at least partially due to the
independent control of the flows of oxidant 68, fuel 70, and
diluent 514 (e.g., exhaust gas). It is believed that various
configurations of diffusion fuel nozzles 554 and diluent injection
(e.g., diluent injection system 770 of FIG. 16) may substantially
increase the operable range of gas turbine loads, throughput of
exhaust gas, and output of the exhaust gas 42 (e.g., streams 95)
for use in the target systems 422, such as the hydrocarbon
production system 12.
ADDITIONAL DESCRIPTION
[0117] By way of example, the following clauses are offered as
further description of the present disclosure:
[0118] Embodiment 1. A system, comprising: a turbine combustor
comprising a first diffusion fuel nozzle, wherein the first
diffusion fuel nozzle is configured to produce a diffusion flame; a
turbine driven by combustion products from the diffusion flame in
the turbine combustor; an exhaust gas compressor, wherein the
exhaust gas compressor is configured to compress and route an
exhaust gas from the turbine to the turbine combustor along an
exhaust recirculation path; and a control system configured to
control flow rates of at least one oxidant and at least one fuel to
the turbine combustor in a stoichiometric control mode and a
non-stoichiometric control mode, wherein the stoichiometric control
mode is configured to change the flow rates and provide a
substantially stoichiometric ratio of the at least one fuel with
the at least one oxidant, and the non-stoichiometric control mode
is configured to change the flow rates and provide a
non-stoichiometric ratio of the at least one fuel with the at least
one oxidant.
[0119] Embodiment 2. The system of embodiment 1, wherein the
stoichiometric control mode is configured to provide the
substantially stoichiometric ratio with an equivalence ratio of
approximately 1.0.
[0120] Embodiment 3. The system of any preceding embodiment,
wherein the stoichiometric control mode is configured to provide
the substantially stoichiometric ratio with an equivalence ratio of
between approximately 0.95 and approximately 1.05.
[0121] Embodiment 4. The system of any preceding embodiment,
wherein the non-stoichiometric control mode is configured to
provide the non-stoichiometric ratio with an equivalence ratio of
less than approximately 0.95 or greater than approximately
1.05.
[0122] Embodiment 5. The system of any preceding embodiment,
wherein the control system is configured to change the flow rates
from a first set of flow rates to a second set of flow rates and
transition between the stoichiometric control mode and the
non-stoichiometric control mode.
[0123] Embodiment 6. The system of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates.
[0124] Embodiment 7. The system of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates.
[0125] Embodiment 8. The system of any preceding embodiment,
wherein the control system in the stoichiometric control mode is
configured to change the flow rates from a first set of flow rates
to a second set of flow rates while maintaining the substantially
stoichiometric ratio.
[0126] Embodiment 9. The system of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates.
[0127] Embodiment 10. The system of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates.
[0128] Embodiment 11. The system of any preceding embodiment,
wherein the control system in the stoichiometric control mode is
configured to change a power output of the turbine from a first
power output to a second power output by changing the flow rates
from the first set of flow rates to the second set of flow rates,
respectively.
[0129] Embodiment 12. The system of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates, and the second power output is less than the first
power output.
[0130] Embodiment 13. The system of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates, and the second power output is greater than the
first power output.
[0131] Embodiment 14. The system of any preceding embodiment,
wherein the control system in the stoichiometric control mode is
configured to maintain emissions in the exhaust gas within one or
more target emissions ranges while changing the flow rates from the
first set of flow rates to the second set of flow rates.
[0132] Embodiment 15. The system of any preceding embodiment,
wherein the emissions comprise carbon monoxide, oxygen, nitrogen
oxides, sulfur oxides, unburnt hydrocarbons, hydrogen, or any
combination thereof.
[0133] Embodiment 16. The system of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 50 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
5000 ppmv.
[0134] Embodiment 17. The system of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 10 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
1000 ppmv.
[0135] Embodiment 18. The system of any preceding embodiment,
wherein the control system in the stoichiometric control mode is
configured to progressively change the flow rates among a plurality
of sets of flow rates while maintaining the substantially
stoichiometric ratio.
[0136] Embodiment 19. The system of any preceding embodiment,
wherein the plurality of sets of flow rates comprise at least three
sets of flow rates.
[0137] Embodiment 20. The system of any preceding embodiment,
wherein the plurality of sets of flow rates comprise at least four
sets of flow rates.
[0138] Embodiment 21. The system of any preceding embodiment,
wherein the control system in the stoichiometric control mode is
configured to maintain the substantially stoichiometric ratio
while: progressively reducing the flow rates among the plurality of
sets of flow rates; progressively reducing a power output of the
turbine among a plurality of power outputs; and maintaining
emissions in the exhaust gas within one or more target emissions
ranges.
[0139] Embodiment 22. The system of any preceding embodiment,
wherein the emissions comprise carbon monoxide, oxygen, nitrogen
oxides, sulfur oxides, unburnt hydrocarbons, hydrogen, or any
combination thereof.
[0140] Embodiment 23. The system of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 50 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
5000 ppmv.
[0141] Embodiment 24. The system of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 10 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
1000 ppmv.
[0142] Embodiment 25. The system of any preceding embodiment,
wherein the control system is configured to transition from the
stoichiometric control mode to the non-stoichiometric control mode
after progressively reducing the flow rates, progressively reducing
the power output, and maintaining emissions.
[0143] Embodiment 26. The system of any preceding embodiment,
wherein, after the transition from the stoichiometric control mode
to the non-stoichiometric control mode, the control system is
configured to operate in a fuel rich control mode of the
non-stoichiometric control mode.
[0144] Embodiment 27. The system of any preceding embodiment,
wherein, after the transition from the stoichiometric control mode
to the non-stoichiometric control mode, the control system is
configured to operate in a fuel lean control mode of the
non-stoichiometric control mode.
[0145] Embodiment 28. The system of any preceding embodiment,
wherein the control system is configured to maintain emissions in
the exhaust gas within a first set of target emissions ranges while
operating in the stoichiometric control mode, the control system is
configured to maintain emissions in the exhaust gas within a second
set of target emissions ranges while operating in the
non-stoichiometric control mode, and the first and second sets of
target emissions ranges are different from one another.
[0146] Embodiment 29. The system of any preceding embodiment,
wherein the non-stoichiometric control mode comprises a fuel lean
control mode having a target emissions range of oxygen emissions
that is at least approximately 1000 parts per million by volume
(ppmv).
[0147] Embodiment 30. The system of any preceding embodiment,
wherein the non-stoichiometric control mode comprises a fuel lean
control mode having a target emissions range of carbon monoxide
emissions that is less than approximately 100 parts per million by
volume (ppmv).
[0148] Embodiment 31. The system of any preceding embodiment,
wherein the non-stoichiometric control mode comprises a fuel lean
control mode having a target emissions range of carbon monoxide
emissions that is less than approximately 20 parts per million by
volume (ppmv).
[0149] Embodiment 32. The system of any preceding embodiment,
wherein the non-stoichiometric control mode comprises a fuel lean
control mode having a target emissions range of nitrogen oxides
emissions that is less than approximately 200 parts per million by
volume (ppmv).
[0150] Embodiment 33. The system of any preceding embodiment,
wherein the non-stoichiometric control mode comprises a fuel lean
control mode having a target emissions range of nitrogen oxides
emissions that is less than approximately 100 parts per million by
volume (ppmv).
[0151] Embodiment 34. The system of any preceding embodiment,
wherein the control system is configured to: progressively change
the flow rates among a plurality of sets of flow rates;
progressively change a power output of the turbine among a
plurality of power outputs in response to the changes in flow
rates; maintain emissions in the exhaust gas within one or more
target emissions ranges before and after the changes in flow rates;
maintain a temperature of the exhaust gas along the exhaust
recirculation path within a target temperature range before and
after the changes in flow rates; and maintain a pressure of the
exhaust gas along the exhaust recirculation path within a target
pressure range before and after the changes in flow rates.
[0152] Embodiment 35. The system of any preceding embodiment,
wherein the control system is configured to maintain the
temperature within the target temperature range downstream from at
least one catalyst unit along the exhaust recirculation path.
[0153] Embodiment 36. The system of any preceding embodiment,
wherein the control system is configured to maintain the pressure
by adjusting at least one of an exhaust extraction valve, an
exhaust vent valve, an operating speed of the exhaust gas
compressor or an oxidant compressor, a position of an inlet guide
vane of the exhaust gas compressor, a recycle valve of the exhaust
gas compressor, or any combination thereof.
[0154] Embodiment 37. The system of any preceding embodiment,
wherein the turbine combustor comprises a first set of fuel nozzles
coupled to a first fluid supply circuit and a second set of fuel
nozzles coupled to a second fluid supply circuit, the first
diffusion nozzle is part of either the first or second set of fuel
nozzles, and the control system is configured to independently
control fluid flows through the first and second fluid supply
circuits.
[0155] Embodiment 38. The system of any preceding embodiment,
wherein the first set of fuel nozzles comprises a single fuel
nozzle, and the second set of fuel nozzles comprises a plurality of
fuel nozzles.
[0156] Embodiment 39. The system of any preceding embodiment,
wherein the first set of fuel nozzles comprises a first plurality
of fuel nozzle, and the second set of fuel nozzles comprises a
second plurality of fuel nozzles.
[0157] Embodiment 40. The system of any preceding embodiment,
wherein the turbine combustor comprises a third set of fuel nozzles
coupled to a third fluid supply circuit, and the control system is
configured to independently control fluid flows through the first,
second, and third fluid supply circuits.
[0158] Embodiment 41. The system of any preceding embodiment,
wherein the control system is configured to independently change
the fluid flows through the first and second fluid supply circuits
at different rates.
[0159] Embodiment 42. The system of any preceding embodiment,
wherein the control system is configured to independently change
the fluid flows through the first and second fluid supply circuits
at equal rates.
[0160] Embodiment 43. The system of any preceding embodiment,
wherein the first set of fuel nozzles comprises at least the first
diffusion fuel nozzle, and the second set of fuel nozzles comprises
a second diffusion fuel nozzle.
[0161] Embodiment 44. The system of any preceding embodiment,
wherein the first set of fuel nozzles comprises at least the first
diffusion fuel nozzle, and the second set of fuel nozzles comprises
a first premix fuel nozzle.
[0162] Embodiment 45. The system of any preceding embodiment,
comprising a first catalyst unit disposed along the exhaust
recirculation path.
[0163] Embodiment 46. The system of any preceding embodiment,
wherein the first catalyst unit is configured to control
concentration levels of oxygen, carbon monoxide, carbon dioxide,
nitrogen oxides, unburnt hydrocarbons, or any combination thereof,
in the exhaust gas.
[0164] Embodiment 47. The system of any preceding embodiment,
wherein the first catalyst unit comprises an oxidation catalyst, a
carbon monoxide reduction catalyst, a nitrogen oxides reduction
catalyst, an aluminum oxide, a zirconium oxide, a silicone oxide, a
titanium oxide, a platinum oxide, a palladium oxide, a cobalt
oxide, or a mixed metal oxide, or a combination thereof.
[0165] Embodiment 48. The system of any preceding embodiment,
wherein the first catalyst unit is configured to drive an oxidizing
reaction with the exhaust gas and an oxidant fuel.
[0166] Embodiment 49. The system of any preceding embodiment,
wherein the control system is configured to adjust a flow of the
oxidant fuel to control the oxidizing reaction.
[0167] Embodiment 50. The system of any preceding embodiment,
wherein the control system is configured to adjust the flow of the
oxidant fuel in response to sensor feedback, and the sensor
feedback comprises gas composition feedback indicative of oxygen,
carbon monoxide, hydrogen, nitrogen oxides, unburnt hydrocarbons,
or any combination thereof.
[0168] Embodiment 51. The system of any preceding embodiment,
comprising a first heat recovery unit, a second heat recovery unit,
or a combination thereof, disposed along the exhaust recirculation
path.
[0169] Embodiment 52. The system of any preceding embodiment,
comprising a first catalyst unit, a second catalyst unit, or a
combination thereof, disposed along the exhaust recirculation
path.
[0170] Embodiment 53. The system of any preceding embodiment,
wherein the first or second catalyst unit is disposed upstream,
downstream, or integrated with the first or second heat recovery
unit.
[0171] Embodiment 54. The system of any preceding embodiment,
comprising the first heat recovery unit having a first heat
recovery steam generator.
[0172] Embodiment 55. The system of any preceding embodiment,
comprising a first steam turbine coupled to the first heat recovery
steam generator.
[0173] Embodiment 56. The system of any preceding embodiment,
comprising the second heat recovery unit having a second heat
recovery steam generator, a first steam turbine coupled to the
first heat recovery steam generator, and a second steam turbine
coupled to the second heat recovery steam generator.
[0174] Embodiment 57. The system of any preceding embodiment,
comprising a moisture removal system and/or a particulate removal
system disposed along the exhaust recirculation path.
[0175] Embodiment 58. The system of any preceding embodiment,
wherein the moisture removal system comprises a heat exchanger, a
condenser, a water gas separator, a first filter, or any
combination thereof, wherein the particulate removal system
comprises an inertial separator, a gravity separator, a second
filter, or any combination thereof.
[0176] Embodiment 59. The system of any preceding embodiment,
comprising a booster blower disposed along the exhaust
recirculation path.
[0177] Embodiment 60. The system of any preceding embodiment,
comprising a heat recovery unit, a booster blower, a moisture
removal unit, and a particulate removal unit disposed along the
exhaust recirculation path.
[0178] Embodiment 61. The system of any preceding embodiment,
wherein the first diffusion fuel nozzle comprises a first fuel
passage and a first oxidant passage that are isolated from one
another along the first diffusion fuel nozzle.
[0179] Embodiment 62. The system of any preceding embodiment,
wherein the first diffusion fuel nozzle comprises a first diluent
passage.
[0180] Embodiment 63. The system of any preceding embodiment,
wherein the first diluent passage is configured to flow a portion
of the exhaust gas through the first diffusion fuel nozzle.
[0181] Embodiment 64. The system of any preceding embodiment,
wherein the first diluent passage is configured to flow a portion
of the exhaust gas, steam, nitrogen, another inert gas, or a
combination thereof, through the first diffusion fuel nozzle.
[0182] Embodiment 65. The system of any preceding embodiment,
wherein the turbine combustor comprises a diluent injection system
disposed downstream from the first diffusion fuel nozzle.
[0183] Embodiment 66. The system of any preceding embodiment,
wherein the diluent injection system is configured to inject a
portion of the exhaust gas, steam, nitrogen, or another inert gas,
or a combination thereof, into a chamber of the turbine combustor
downstream from the first diffusion fuel nozzle.
[0184] Embodiment 67. The system of any preceding embodiment,
wherein the diluent injection system comprises a plurality of
openings in a liner of the turbine combustor, and the plurality of
openings is configured to inject the portion of the exhaust gas
into the chamber of the turbine combustor.
[0185] Embodiment 68. The system of any preceding embodiment,
wherein the turbine combustor comprises a first wall disposed about
the chamber, a second wall disposed about the first wall, and an
exhaust passage disposed between the first and second walls,
wherein the diluent injection system comprises a plurality of
diluent injectors extending through the first and second walls of
the turbine combustor.
[0186] Embodiment 69. The system of any preceding embodiment,
wherein the plurality of diluent injectors is configured inject the
portion of the exhaust gas, steam, nitrogen, or another inert gas
into the chamber of the turbine combustor.
[0187] Embodiment 70. The system of any preceding embodiment,
comprising an exhaust gas extraction system configured to extract a
portion of the exhaust gas.
[0188] Embodiment 71. The system of any preceding embodiment,
comprising an exhaust gas treatment system configured to treat the
portion of the exhaust gas.
[0189] Embodiment 72. The system of any preceding embodiment,
wherein the exhaust gas treatment system comprises a gas separation
system configured to separate the portion of the exhaust gas into a
plurality of gas streams.
[0190] Embodiment 73. The system of any preceding embodiment,
wherein the plurality of gas streams comprises a first stream that
is carbon dioxide (CO.sub.2) rich and a second stream that is
carbon dioxide (CO.sub.2) lean.
[0191] Embodiment 74. The system of any preceding embodiment,
wherein the exhaust gas treatment system comprises a gas
compression system, a moisture removal system, a particulate
removal system, or a combination thereof, configured to receive at
least one of the first or second streams.
[0192] Embodiment 75. The system of any preceding embodiment,
wherein the exhaust gas treatment system comprises a gas
purification system configured to purify at least one of the
plurality of gas streams.
[0193] Embodiment 76. The system of any preceding embodiment,
comprising a target system configured to receive at least one of
the plurality of streams, wherein the target system comprises a
hydrocarbon production system, a subterranean reservoir, a carbon
sequestration system, a pipeline, a storage tank, or any
combination thereof.
[0194] Embodiment 77. The system of any preceding embodiment,
wherein the exhaust gas treatment system comprises a compression
system configured to compress the portion of the exhaust gas.
[0195] Embodiment 78. The system of any preceding embodiment,
wherein the exhaust gas treatment system comprises a moisture
removal system and/or a particulate removal system.
[0196] Embodiment 79. The system of any preceding embodiment,
comprising a control system responsive to sensor feedback to adjust
one or more operating parameters to control an equivalence ratio or
emissions levels in the exhaust gas.
[0197] Embodiment 80. The system of any preceding embodiment,
wherein the one or more operating parameters comprise an oxidant
flow rate and/or a fuel flow rate to the turbine combustor.
[0198] Embodiment 81. The system of any preceding embodiment,
wherein the control system is configured to maintain the
equivalence ratio between approximately 0.95 and 1.05.
[0199] Embodiment 82. The system of any preceding embodiment,
wherein the sensor feedback comprises gas composition feedback
relating to oxygen, carbon monoxide, hydrogen, nitrogen oxides,
unburnt hydrocarbons, or any combination thereof.
[0200] Embodiment 83. The system of any preceding embodiment,
wherein the control system is coupled to a plurality of sensors
configured to obtain the sensor feedback, and the plurality of
sensors are disposed along the exhaust recirculation path, the
turbine combustor, the turbine, the exhaust gas compressor, or a
combination thereof.
[0201] Embodiment 84. The system of any preceding embodiment,
comprising a bypass line from the exhaust gas compressor to the
turbine, wherein the bypass line comprises a heat exchanger
configured to cool a bypass flow of the exhaust gas from the
exhaust gas compressor to the turbine.
[0202] Embodiment 85. The system of any preceding embodiment,
comprising a gas turbine engine having the turbine combustor, the
turbine, and the exhaust gas compressor, wherein the gas turbine
engine is a stoichiometric exhaust gas recirculation (SEGR) gas
turbine engine.
[0203] Embodiment 86. The system of any preceding embodiment,
comprising an exhaust gas extraction system coupled to the gas
turbine engine, an exhaust gas treatment system coupled to the
exhaust gas extraction system, and a hydrocarbon production system
coupled to the exhaust gas treatment system.
[0204] Embodiment 87. A method, comprising: injecting at least one
oxidant and at least one fuel into a chamber of a turbine
combustor, wherein the at least one oxidant and the at least one
fuel mix and combust as a diffusion flame to generate combustion
products; driving a turbine with the combustion products and
outputting an exhaust gas; recirculating the exhaust gas along an
exhaust recirculation path to an exhaust gas compressor;
compressing and routing the exhaust gas to the turbine combustor;
controlling flow rates of the at least one oxidant and the at least
one fuel to the turbine combustor in a stoichiometric control mode,
wherein the stoichiometric control mode is configured to change the
flow rates and provide a substantially stoichiometric ratio of the
at least one fuel with the at least one oxidant; and controlling
flow rates of the at least one oxidant and the at least one fuel to
the turbine combustor in a non-stoichiometric control mode, wherein
the non-stoichiometric control mode is configured to change the
flow rates and provide a non-stoichiometric ratio of the at least
one fuel with the at least one oxidant.
[0205] Embodiment 88. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
providing the substantially stoichiometric ratio with an
equivalence ratio of approximately 1.0.
[0206] Embodiment 89. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
providing the substantially stoichiometric ratio with an
equivalence ratio of between approximately 0.95 and approximately
1.05.
[0207] Embodiment 90. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises providing the non-stoichiometric ratio with an
equivalence ratio of less than approximately 0.95 or greater than
approximately 1.05.
[0208] Embodiment 91. The method of any preceding embodiment,
comprising changing the flow rates from a first set of flow rates
to a second set of flow rates and transitioning between the
stoichiometric control mode and the non-stoichiometric control
mode.
[0209] Embodiment 92. The method of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates.
[0210] Embodiment 93. The method of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates.
[0211] Embodiment 94. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
changing the flow rates from a first set of flow rates to a second
set of flow rates while maintaining the substantially
stoichiometric ratio.
[0212] Embodiment 95. The method of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates.
[0213] Embodiment 96. The method of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates.
[0214] Embodiment 97. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
changing a power output of the turbine from a first power output to
a second power output by changing the flow rates from the first set
of flow rates to the second set of flow rates, respectively.
[0215] Embodiment 98. The method of any preceding embodiment,
wherein the second set of flow rates is less than the first set of
flow rates, and the second power output is less than the first
power output.
[0216] Embodiment 99. The method of any preceding embodiment,
wherein the second set of flow rates is greater than the first set
of flow rates, and the second power output is greater than the
first power output.
[0217] Embodiment 100. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
changing maintaining emissions in the exhaust gas within one or
more target emissions ranges while changing the flow rates from the
first set of flow rates to the second set of flow rates.
[0218] Embodiment 101. The method of any preceding embodiment,
wherein the emissions comprise carbon monoxide, oxygen, nitrogen
oxides, sulfur oxides, unburnt hydrocarbons, hydrogen, or any
combination thereof.
[0219] Embodiment 102. The method of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 50 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
5000 ppmv.
[0220] Embodiment 103. The method of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 10 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
1000 ppmv.
[0221] Embodiment 104. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
progressively changing the flow rates among a plurality of sets of
flow rates while maintaining the substantially stoichiometric
ratio.
[0222] Embodiment 105. The method of any preceding embodiment,
wherein the plurality of sets of flow rates comprise at least three
sets of flow rates.
[0223] Embodiment 106. The method of any preceding embodiment,
wherein the plurality of sets of flow rates comprise at least four
sets of flow rates.
[0224] Embodiment 107. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
maintaining the substantially stoichiometric ratio while:
progressively reducing the flow rates among the plurality of sets
of flow rates; progressively reducing a power output of the turbine
among a plurality of power outputs; and maintaining emissions in
the exhaust gas within one or more target emissions ranges.
[0225] Embodiment 108. The method of any preceding embodiment,
wherein the emissions comprise carbon monoxide, oxygen, nitrogen
oxides, sulfur oxides, unburnt hydrocarbons, hydrogen, or any
combination thereof.
[0226] Embodiment 109. The method of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 50 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
5000 ppmv.
[0227] Embodiment 110. The method of any preceding embodiment,
wherein the one or more target emissions ranges comprise an oxygen
range of less than approximately 10 parts per million by volume
(ppmv) and/or a carbon monoxide range of less than approximately
1000 ppmv.
[0228] Embodiment 111. The method of any preceding embodiment,
comprising transitioning from the stoichiometric control mode to
the non-stoichiometric control mode after progressively reducing
the flow rates, progressively reducing the power output, and
maintaining emissions.
[0229] Embodiment 112. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel rich control mode after the
transition from the stoichiometric control mode to the
non-stoichiometric control mode.
[0230] Embodiment 113. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode after the
transition from the stoichiometric control mode to the
non-stoichiometric control mode.
[0231] Embodiment 114. The method of any preceding embodiment,
wherein controlling in the stoichiometric control mode comprises
maintaining emissions in the exhaust gas within a first set of
target emissions ranges, wherein controlling in the
non-stoichiometric control mode comprises maintaining emissions in
the exhaust gas within a second set of target emissions ranges,
wherein the first and second sets of target emissions ranges are
different from one another.
[0232] Embodiment 115. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode having a target
emissions range of oxygen emissions that is at least approximately
1000 parts per million by volume (ppmv).
[0233] Embodiment 116. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode having a target
emissions range of carbon monoxide emissions that is less than
approximately 100 parts per million by volume (ppmv).
[0234] Embodiment 117. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode having a target
emissions range of carbon monoxide emissions that is less than
approximately 20 parts per million by volume (ppmv).
[0235] Embodiment 118. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode having a target
emissions range of nitrogen oxides emissions that is less than
approximately 200 parts per million by volume (ppmv).
[0236] Embodiment 119. The method of any preceding embodiment,
wherein controlling in the non-stoichiometric control mode
comprises operating in a fuel lean control mode having a target
emissions range of nitrogen oxides emissions that is less than
approximately 100 parts per million by volume (ppmv).
[0237] Embodiment 120. The method of any preceding embodiment,
comprising controlling one or more operational parameters for:
progressively changing the flow rates among a plurality of sets of
flow rates; progressively changing a power output of the turbine
among a plurality of power outputs in response to changing the flow
rates; maintaining emissions in the exhaust gas within one or more
target emissions ranges before and after changing the flow rates;
maintaining a temperature of the exhaust gas along the exhaust
recirculation path within a target temperature range before and
after changing the flow rates; and maintaining a pressure of the
exhaust gas along the exhaust recirculation path within a target
pressure range before and after changing the flow rates.
[0238] Embodiment 121. The method of any preceding embodiment,
wherein controlling comprises maintaining the temperature within
the target temperature range downstream from at least one catalyst
unit along the exhaust recirculation path.
[0239] Embodiment 122. The method of any preceding embodiment,
comprising controlling comprises maintaining the pressure by
adjusting at least one of an exhaust extraction valve, an exhaust
vent valve, an operating speed of the exhaust gas compressor or an
oxidant compressor, a position of an inlet guide vane of the
exhaust gas compressor, a recycle valve of the exhaust gas
compressor, or any combination thereof.
[0240] Embodiment 123. The method of any preceding embodiment,
comprising independently controlling fluid flows through first and
second fluid supply circuits, wherein the turbine combustor
comprises a first set of fuel nozzles coupled to the first fluid
supply circuit and a second set of fuel nozzles coupled to the
second fluid supply circuit, wherein at least one of the first or
second set of fuel nozzles comprises a first diffusion fuel nozzle
configured to generate the diffusion flame.
[0241] Embodiment 124. The method of any preceding embodiment,
wherein the first set of fuel nozzles comprises a single fuel
nozzle, and the second set of fuel nozzles comprises a plurality of
fuel nozzles.
[0242] Embodiment 125. The method of any preceding embodiment,
wherein the first set of fuel nozzles comprises a first plurality
of fuel nozzle, and the second set of fuel nozzles comprises a
second plurality of fuel nozzles.
[0243] Embodiment 126. The method of any preceding embodiment,
comprising independently controlling fluid flows through the first
fluid supply circuit, the second fluid supply circuit, and a third
fluid supply circuit, wherein the turbine combustor comprises a
third set of fuel nozzles coupled to the third fluid supply
circuit.
[0244] Embodiment 127. The method of any preceding embodiment,
comprising independently changing the fluid flows through the first
and second fluid supply circuits at different rates.
[0245] Embodiment 128. The method of any preceding embodiment,
comprising independently changing the fluid flows through the first
and second fluid supply circuits at equal rates.
[0246] Embodiment 129. The method of any preceding embodiment,
wherein the first set of fuel nozzles comprises at least the first
diffusion fuel nozzle, and the second set of fuel nozzles comprises
a second diffusion fuel nozzle.
[0247] Embodiment 130. The method of any preceding embodiment,
wherein the first set of fuel nozzles comprises at least the first
diffusion fuel nozzle, and the second set of fuel nozzles comprises
a first premix fuel nozzle.
[0248] Embodiment 131. The method of any preceding embodiment,
wherein injecting comprises separately injecting the at least one
oxidant and the at least one fuel from respective first and second
passages that are isolated from one another along a first diffusion
fuel nozzle.
[0249] Embodiment 132. The method of any preceding embodiment,
wherein the first and second passages are disposed in a concentric
arrangement.
[0250] Embodiment 133. The method of any preceding embodiment,
wherein the first passage extends around the second passage.
[0251] Embodiment 134. The method of any preceding embodiment,
wherein the second passage extends around the first passage.
[0252] Embodiment 135. The method of any preceding embodiment,
comprising injecting at least one diluent into the chamber.
[0253] Embodiment 136. The method of any preceding embodiment,
wherein the at least one diluent comprises a portion of the exhaust
gas, steam, nitrogen, another inert gas, or a combination
thereof.
[0254] Embodiment 137. The method of any preceding embodiment,
comprising separately injecting the at least one oxidant and the at
least one fuel from respective first and second passages that are
isolated from one another along a first diffusion fuel nozzle, and
routing a diluent flow through the first diffusion fuel nozzle.
[0255] Embodiment 138. The method of any preceding embodiment,
comprising routing a diluent flow into the chamber downstream from
a first diffusion fuel nozzle.
[0256] Embodiment 139. The method of any preceding embodiment,
comprising injecting the diluent flow through a plurality of
openings in a liner of the turbine combustor, and the diluent flow
comprises a portion of the exhaust gas.
[0257] Embodiment 140. The method of any preceding embodiment,
comprising injecting the diluent flow through a plurality of
diluent injectors extending through at least one wall of the
turbine combustor, and the diluent flow comprises a portion of the
exhaust gas, steam, nitrogen, or another inert gas.
[0258] Embodiment 141. The method of any preceding embodiment,
comprising treating the exhaust gas with a first catalyst unit
along the exhaust recirculation path.
[0259] Embodiment 142. The method of any preceding embodiment,
wherein treating comprises controlling concentration levels of
carbon monoxide, carbon dioxide, and unburnt hydrocarbons in the
exhaust gas.
[0260] Embodiment 143. The method of any preceding embodiment,
wherein treating comprises driving an oxidizing reaction with the
exhaust gas and an oxidant fuel.
[0261] Embodiment 144. The method of any preceding embodiment,
comprising controlling a flow of the oxidant fuel to the first
catalyst unit to control the oxidizing reaction.
[0262] Embodiment 145. The method of any preceding embodiment,
comprising controlling the flow of the oxidant fuel in response to
sensor feedback, and the sensor feedback comprises gas composition
feedback indicative of oxygen, carbon monoxide, hydrogen, nitrogen
oxides, unburnt hydrocarbons, or any combination thereof.
[0263] Embodiment 146. The method of any preceding embodiment,
comprising recovering heat from the exhaust gas along the exhaust
recirculation path using a first heat recovery unit, a second heat
recovery unit, or a combination thereof.
[0264] Embodiment 147. The method of any preceding embodiment,
comprising driving a first catalytic reaction with a first catalyst
unit within, upstream, or downstream of the first or second heat
recovery unit.
[0265] Embodiment 148. The method of any preceding embodiment,
comprising driving a second catalytic reaction with a second
catalyst unit within, upstream, or downstream of the first or
second heat recovery unit.
[0266] Embodiment 149. The method of any preceding embodiment,
comprising generating a first steam with a first heat recovery
steam generator of the first heat recovery unit, generating a
second steam with a second heat recovery steam generator of the
second heat recovery unit, or a combination thereof.
[0267] Embodiment 150. The method of any preceding embodiment,
comprising driving a first steam turbine with the first steam or
driving a second steam turbine with the second steam.
[0268] Embodiment 151. The method of any preceding embodiment,
comprising removing moisture from the exhaust gas with a moisture
removal system disposed along the exhaust recirculation path.
[0269] Embodiment 152. The method of any preceding embodiment,
wherein the moisture removal system comprises a heat exchanger, a
condenser, a water gas separator, a filter, or any combination
thereof.
[0270] Embodiment 153. The method of any preceding embodiment,
comprising removing particulate from the exhaust gas with a
particulate removal system disposed along the exhaust recirculation
path.
[0271] Embodiment 154. The method of any preceding embodiment,
wherein the particulate removal system comprises an inertial
separator, a gravity separator, a filter, or any combination
thereof.
[0272] Embodiment 155. The method of any preceding embodiment,
comprising boosting a flow of the exhaust gas with a booster blower
disposed along the exhaust recirculation path.
[0273] Embodiment 156. The method of any preceding embodiment,
comprising a heat recovery unit, a booster blower, a moisture
removal unit, and a particulate removal unit disposed along the
exhaust recirculation path.
[0274] Embodiment 157. The method of any preceding embodiment,
comprising extracting a portion of the exhaust gas with an exhaust
gas extraction system.
[0275] Embodiment 158. The method of any preceding embodiment,
comprising treating the portion of the exhaust gas with an exhaust
gas treatment system.
[0276] Embodiment 159. The method of any preceding embodiment,
wherein treating the portion of the exhaust gas comprises
separating the portion of the exhaust gas into a plurality of gas
streams.
[0277] Embodiment 160. The method of any preceding embodiment,
wherein the plurality of gas streams comprises a first stream that
is carbon dioxide (CO.sub.2) rich and a second stream that is
carbon dioxide (CO.sub.2) lean.
[0278] Embodiment 161. The method of any preceding embodiment,
wherein treating the portion of the exhaust gas comprises
compressing the portion of the exhaust gas, the first stream, or
the second steam with a gas compression system.
[0279] Embodiment 162. The method of any preceding embodiment,
wherein treating the portion of the exhaust gas comprises removing
moisture from the portion of the exhaust gas, the first stream, or
the second steam with a moisture removal system.
[0280] Embodiment 163. The method of any preceding embodiment,
wherein treating the portion of the exhaust gas comprises removing
particulate from the portion of the exhaust gas, the first stream,
or the second steam with a particulate removal system.
[0281] Embodiment 164. The method of any preceding embodiment,
comprising routing the portion of the exhaust gas, the first
stream, or the second steam to a target system, wherein the target
system comprises a hydrocarbon production system, a subterranean
reservoir, a carbon sequestration system, a pipeline, a storage
tank, or any combination thereof.
[0282] Embodiment 165. The method of any preceding embodiment,
comprising adjusting one or more operating parameters in response
to sensor feedback to control an equivalence ratio or emissions
levels in the exhaust gas.
[0283] Embodiment 166. The method of any preceding embodiment,
comprising obtaining the sensor feedback by monitoring a gas
composition of the exhaust gas relating to oxygen, carbon monoxide,
hydrogen, nitrogen oxides, unburnt hydrocarbons, or any combination
thereof.
[0284] Embodiment 167. The method of any preceding embodiment,
wherein obtaining the sensor feedback comprises monitoring a
plurality of sensors disposed along the exhaust recirculation path,
the turbine combustor, the turbine, the exhaust gas compressor, or
a combination thereof.
[0285] Embodiment 168. The method of any preceding embodiment,
comprising routing a bypass flow of the exhaust gas along a bypass
line from the exhaust gas compressor to the turbine.
[0286] Embodiment 169. The method of any preceding embodiment,
comprising cooling the bypass flow of the exhaust gas along the
bypass line, and cooling the turbine using the bypass flow of the
exhaust gas.
[0287] Embodiment 170. The method of any preceding embodiment,
comprising operating a gas turbine engine having the turbine
combustor, the turbine, and the exhaust gas compressor to achieve
substantially stoichiometric combustion based on sensor feedback
during the stoichiometric control mode.
[0288] Embodiment 171. The method of any preceding embodiment,
comprising extracting a portion of the exhaust gas with an exhaust
gas extraction system coupled to the gas turbine engine, and
routing the portion of the exhaust gas to a hydrocarbon production
system, a carbon sequestration system, a pipeline, a storage tank,
or any combination thereof.
[0289] Embodiment 172. A method, comprising: introducing an oxidant
to at least one oxidant compressor to produce a compressed oxidant
stream; introducing a recirculated low oxygen content gas stream to
a compressor section of a gas turbine engine to produce a
compressed low oxygen content gas stream; introducing a first
portion of the compressed oxidant stream with a first compressed
oxidant flow rate and a fuel stream with a first fuel flow rate in
a substantially stoichiometric ratio to at least one turbine
combustor and mixing the compressed oxidant stream and the fuel
stream at the point of combustion and combusting the mixture of the
compressed oxidant stream and the fuel stream; introducing a first
portion of the compressed low oxygen content gas stream with a low
oxygen content gas flow rate to the at least one turbine combustor
and mixing it with the combusting streams of compressed oxidant and
fuel after the point of combustion and producing a high temperature
high pressure low oxygen content stream; introducing the high
temperature high pressure low oxygen content stream to an expander
section of the gas turbine engine and expanding the high
temperature high pressure low oxygen content stream to produce a
first mechanical power and a recirculated low oxygen content gas
stream at a first recirculated low oxygen content gas flow rate
wherein the recirculated low oxygen content gas stream contains a
first recirculated low oxygen content gas emissions level; using a
first portion of the first mechanical power to drive the compressor
section of the gas turbine engine; using a second portion of the
first mechanical power to drive at least one of: a generator, the
at least one oxidant compressor or at least one other mechanical
device; recirculating the recirculated low oxygen content gas
stream in a recirculation loop from the outlet of the expander
section to the inlet of the compressor section of the gas turbine
engine; extracting at least a second portion of the compressed low
oxygen content gas stream from the gas turbine engine and
delivering the at least a second portion of the compressed low
oxygen content gas stream to the first at least one oxidation
catalyst unit and producing a low oxygen content product stream
comprising a first low oxygen content product emissions level that
is within a target range; reducing fuel stream flow rate to a
second fuel stream flow rate that is less than the first fuel
stream flow rate and reducing the first portion of the compressed
oxidant stream flow rate to a second compressed oxidant flow rate
that is less than the first compressed oxidant flow rate, wherein
the substantially stoichiometric ratio is maintained, producing a
second mechanical power that is less than the first mechanical
power and producing a low oxygen content product stream comprising
a second low oxygen content product emissions level that is within
a target range; reducing fuel stream flow rate to a third fuel
stream flow rate that is less than the second fuel stream flow rate
and reducing the first portion of the compressed oxidant stream
flow rate to a third compressed oxidant flow rate that is less than
the second compressed oxidant flow rate, wherein the substantially
stoichiometric ratio is maintained, producing a third mechanical
power that is less than the second mechanical power and producing a
low oxygen content product stream comprising a third low oxygen
content product emissions level that is at the limit of a target
range; and reducing fuel stream flow rate to a fourth fuel stream
flow rate that is less than the third fuel stream flow rate and
reducing the first portion of the compressed oxidant stream flow
rate to a fourth compressed oxidant flow rate that is less than the
third compressed oxidant flow rate, wherein the substantially
stoichiometric ratio is not maintained and fuel lean combustion is
achieved, producing a fourth mechanical power that is less than the
third mechanical power and producing a high oxygen content product
stream comprising a high oxygen content product emissions
level.
[0290] Embodiment 173. The method of any preceding embodiment,
wherein the first recirculated low oxygen content gas emissions
comprises at least one of oxygen, carbon monoxide, hydrogen, oxides
of nitrogen, unburned hydrocarbons or similar products of
incomplete combustion.
[0291] Embodiment 174. The method of any preceding embodiment,
wherein the first, second and third low oxygen content product
emissions comprises at least one of oxygen, carbon monoxide,
hydrogen, oxides of nitrogen, unburned hydrocarbons or similar
products of incomplete combustion.
[0292] Embodiment 175. The method of any preceding embodiment,
wherein the high oxygen content product emissions comprises at
least one of oxygen, carbon monoxide, hydrogen, oxides of nitrogen,
unburned hydrocarbons or similar products of incomplete
combustion.
[0293] Embodiment 176. The method of any preceding embodiment,
wherein the limit of the low oxygen content product emissions level
is at least one of 50 ppmv oxygen and 5000 ppmv carbon
monoxide.
[0294] Embodiment 177. The method of any preceding embodiment,
wherein the limit of the low oxygen content product emissions level
is at least one of 10 ppmv oxygen and 1000 ppmv carbon
monoxide.
[0295] Embodiment 178. The method of any preceding embodiment,
wherein the high oxygen content product emissions level comprises
at least 1000 ppmv oxygen.
[0296] Embodiment 179. The method of any preceding embodiment,
wherein the high oxygen content product emissions level comprises
less than 100 ppmv carbon monoxide.
[0297] Embodiment 180. The method of any preceding embodiment,
wherein the high oxygen content product emissions level comprises
less than 20 ppmv carbon monoxide.
[0298] Embodiment 181. The method of any preceding embodiment,
wherein the high oxygen content product emissions level comprises
less than 200 ppmv nitrogen oxides.
[0299] Embodiment 182. The method of any preceding embodiment,
wherein the high oxygen content product emissions level comprises
less than 100 ppmv nitrogen oxides.
[0300] Embodiment 183. The method of any preceding embodiment,
comprising introducing a second portion of the compressed oxidant
stream to the first at least one oxidation catalyst unit to oxidize
at least a portion of the at least one of carbon monoxide,
hydrogen, unburned hydrocarbons or similar products of incomplete
combustion contained in the second portion of the compressed low
oxygen content stream.
[0301] Embodiment 184. The method of any preceding embodiment,
comprising introducing an oxidation fuel to the first at least one
oxidation catalyst unit and reducing at least a portion of the
residual oxygen contained in the second portion of the compressed
low oxygen content stream.
[0302] Embodiment 185. The method of any preceding embodiment,
wherein the oxidant consists of essentially ambient air and the
recirculated low oxygen content gas stream comprising comprises
nitrogen.
[0303] Embodiment 186. The method of any preceding embodiment,
wherein the equivalence ratio (phi, #) is equal to (mol % fuel/mol
% oxidant)actual/(mol % fuel/mol % oxidant)stoichiometric.
[0304] Embodiment 187. The method of any preceding embodiment,
comprising controlling the flow rate of at least one of the first
portion of the compressed oxidant stream and the fuel stream to
achieve a combustion equivalence ratio of about 1 and producing a
substantially stoichiometric ratio of the first portion of the
compressed oxidant stream and the fuel stream.
[0305] Embodiment 188. The method of any preceding embodiment,
comprising sensors installed in the recirculation loop and
measuring the constituents within the recirculated low oxygen
content stream.
[0306] Embodiment 189. The method of any preceding embodiment,
wherein the measured constituents are at least one of: oxygen,
carbon monoxide, hydrogen, nitrogen oxides, and unburned
hydrocarbons.
[0307] Embodiment 190. The method of any preceding embodiment,
comprising determining the equivalence ratio by analyzing the
constituent measurements.
[0308] Embodiment 191. The method of any preceding embodiment,
comprising at least one sensor installed and measuring the
constituents within the extracted second portion of the compressed
low oxygen content gas stream upstream of the first at least one
oxidation catalyst unit, downstream of the first at least one
oxidation catalyst unit or both.
[0309] Embodiment 192. The method of any preceding embodiment,
wherein the measured constituents are at least one of: oxygen,
carbon monoxide, hydrogen, nitrogen oxides, and unburned
hydrocarbons.
[0310] Embodiment 193. The method of any preceding embodiment,
comprising at least one controller adjusting at least one of the
combustion equivalence ratio, the flow rate of the second portion
of the compressed oxidant stream or the flow rate of the oxidation
fuel and achieving a desired level of at least one of the measured
constituents downstream of the first at least one oxidation
catalyst unit.
[0311] Embodiment 194. The method of any preceding embodiment,
comprising a first heat recovery unit downstream of the first at
least one oxidation catalyst unit.
[0312] Embodiment 195. The method of any preceding embodiment,
wherein the first heat recovery unit comprises a steam
generator.
[0313] Embodiment 196. The method of any preceding embodiment,
comprising producing steam by the steam generator that is delivered
to at least one steam turbine and driving at least one of a
generator to produce electrical power or another mechanical
device.
[0314] Embodiment 197. The method of any preceding embodiment,
comprising a second heat recovery unit in the recirculation loop
between the outlet of the expander section and the inlet to the
compressor section of the gas turbine engine and removing heat from
the recirculated low oxygen content gas stream.
[0315] Embodiment 198. The method of any preceding embodiment,
wherein the second heat recovery unit comprises a steam
generator.
[0316] Embodiment 199. The method of any preceding embodiment,
comprising producing steam by the steam generator that is delivered
to at least one steam turbine and driving at least one of a
generator to produce electrical power or another mechanical
device.
[0317] Embodiment 200. The method of any preceding embodiment,
comprising a secondary flow path delivering a third portion of the
compressed low oxygen content gas stream from the compressor
section of the gas turbine engine to the turbine as a secondary
flow and after cooling and sealing the turbine delivering the third
portion of the compressed low oxygen content gas stream into the
recirculation loop.
[0318] Embodiment 201. The method of any preceding embodiment,
comprising a booster blower in the recirculation loop increasing
the pressure of the recirculated low oxygen content gas stream
downstream of the second heat recovery unit.
[0319] Embodiment 202. The method of any preceding embodiment,
comprising a heat exchanger within the recirculation loop upstream
of the compressor section of the gas turbine engine cooling the
recirculated low oxygen content gas stream before entering the
inlet of the compressor section of the gas turbine engine.
[0320] Embodiment 203. The method of any preceding embodiment,
comprising condensing and removing water from the recirculated low
oxygen content gas stream with the heat exchanger.
[0321] Embodiment 204. The method of any preceding embodiment,
comprising delivering at least a portion of the low oxygen content
product stream to a subterranean reservoir for enhanced hydrocarbon
recovery.
[0322] Embodiment 205. The method of any preceding embodiment,
comprising compressing the at least a portion of the low oxygen
content product stream with at least one inert gas product
compressor prior to delivering the at least a portion of the low
oxygen content product stream to a subterranean reservoir for
enhanced hydrocarbon recovery.
[0323] Embodiment 206. The method of any preceding embodiment,
comprising cooling the low oxygen content product stream by the
first heat recovery unit.
[0324] Embodiment 207. The method of any preceding embodiment,
comprising delivering the at least a portion of the low oxygen
content product stream to a gas dehydration unit.
[0325] Embodiment 208. The method of any preceding embodiment,
comprising delivering at least a portion of the low oxygen content
product stream to a carbon dioxide separation unit to produce a
lean carbon dioxide stream and a rich carbon dioxide stream.
[0326] Embodiment 209. The method of any preceding embodiment,
comprising delivering at least a portion of the lean carbon dioxide
stream to a subterranean reservoir for enhanced hydrocarbon
recovery.
[0327] Embodiment 210. The method of any preceding embodiment,
comprising delivering at least a portion of the rich carbon dioxide
stream to a subterranean reservoir for enhanced hydrocarbon
recovery.
[0328] Embodiment 211. The method of any preceding embodiment,
comprising delivering at least a portion of the rich carbon dioxide
stream to a carbon sequestration unit.
[0329] Embodiment 212. The method of any preceding embodiment,
comprising compressing the at least a portion of the lean carbon
dioxide stream to at least one lean product compressor prior to
delivering the lean carbon dioxide stream to a subterranean
reservoir for enhanced hydrocarbon recovery.
[0330] Embodiment 213. The method of any preceding embodiment,
comprising compressing the at least a portion of the rich carbon
dioxide stream to at least one rich product compressor prior to
delivering the rich carbon dioxide stream to a subterranean
reservoir for enhanced hydrocarbon recovery.
[0331] Embodiment 214. The method of any preceding embodiment,
comprising compressing the at least a portion of the rich carbon
dioxide stream to at least one rich product compressor prior to
delivering the rich carbon dioxide stream to a carbon sequestration
unit.
[0332] Embodiment 215. The method of any preceding embodiment,
comprising delivering at least a portion of the lean carbon dioxide
stream to a gas dehydration unit.
[0333] Embodiment 216. The method of any preceding embodiment,
comprising delivering at least a portion of the rich carbon dioxide
stream to a gas dehydration unit.
[0334] Embodiment 217. The method of any preceding embodiment,
comprising introducing at least a portion of the low oxygen content
product stream to an expander and expanding the at least a portion
of the low oxygen content product stream, driving at least one of a
generator or another mechanical device and producing a vent
stream.
[0335] Embodiment 218. The method of any preceding embodiment,
comprising introducing at least a portion of the lean carbon
dioxide stream to an expander and expanding the at least a portion
of the lean carbon dioxide stream, driving at least one of a
generator or another mechanical device and producing a vent
stream.
[0336] Embodiment 219. The method of any preceding embodiment,
comprising a second at least one oxidation catalyst unit located
within the recirculation loop and oxidizing at least a portion of
the at least one of carbon monoxide, hydrogen, unburned
hydrocarbons or similar products of incomplete combustion contained
in the recirculated low oxygen content gas stream.
[0337] Embodiment 220. The method of any preceding embodiment,
wherein the second at least one oxidation catalyst unit is located
upstream of the second heat recovery unit.
[0338] Embodiment 221. The method of any preceding embodiment,
wherein the second at least one oxidation catalyst unit is located
downstream of the second heat recovery unit.
[0339] Embodiment 222. The method of any preceding embodiment,
wherein the second at least one oxidation catalyst unit is located
within the second heat recovery unit at a location providing a
suitable operating temperature and providing a suitable heat sink
for the heat generated by the catalytic reactions.
[0340] Embodiment 223. The method of any preceding embodiment,
comprising controlling the flow rate of the at least a second
portion of the compressed low oxygen content gas stream.
[0341] Embodiment 224. The method of any preceding embodiment,
wherein the flow rate of the at least a second portion of the
compressed low oxygen content gas stream is adjusted to maintain
the pressure at a location within the recirculation loop within a
desired range.
[0342] Embodiment 225. The method of any preceding embodiment,
wherein the flow rate of the at least a second portion of the
compressed low oxygen content gas stream is adjusted by means of at
least one of an extraction valve, extraction vent valve, product
compressor operating speed, product compressor inlet guide vane
position or product compressor recycle valve.
[0343] Embodiment 226. The method of any preceding embodiment,
wherein each of the at least one turbine combustor is comprising a
plurality of burners and at least two separately controlled fuel
circuits supplying a fuel stream separately to at least one of two
individual burners, one individual burner and one group of burners,
two groups of burners, and combinations thereof.
[0344] Embodiment 227. The method of any preceding embodiment,
wherein the percentage reduction of fuel flow rate from at least
one of the first fuel flow rate to the second fuel flow rate, the
second fuel flow rate to the third fuel flow rate and the third
fuel flow rate to the fourth fuel flow rate is not equal among the
at least two separately controlled fuel circuits.
[0345] Embodiment 228. The method of any preceding embodiment,
comprising: reducing fuel stream flow rate to a fifth stream flow
rate that is less than the first fuel stream flow rate and reducing
the first portion of the compressed oxidant stream flow rate to a
fifth compressed oxidant flow rate that is less than the first
compressed oxidant flow rate, wherein the substantially
stoichiometric ratio is maintained, producing a fifth mechanical
power that is less than the first mechanical power and producing a
low oxygen content product stream comprising a fifth low oxygen
content product emissions level that is within a target range and a
first heat release from the second at least one oxidation catalyst
unit resulting in a temperature of the recirculated low oxygen
content gas stream downstream of the second at least one oxidation
catalyst unit that is within a target range; reducing fuel stream
flow rate to a sixth fuel stream flow rate that is less than the
fifth fuel stream flow rate and reducing the first portion of the
compressed oxidant stream flow rate to a sixth compressed oxidant
flow rate that is less than the fifth compressed oxidant flow rate,
wherein the substantially stoichiometric ratio is maintained,
producing a sixth mechanical power that is less than the fifth
mechanical power and producing a low oxygen content product stream
comprising a sixth low oxygen content product emissions level that
is within a target range and a second heat release from the second
at least one oxidation catalyst unit resulting in a temperature of
the recirculated low oxygen content gas stream downstream of the
second at least one oxidation catalyst unit that is at the limit of
a target range; reducing fuel stream flow rate to a seventh fuel
stream flow rate that is less than the sixth fuel stream flow rate
and reducing the first portion of the compressed oxidant stream
flow rate to a seventh compressed oxidant flow rate that is less
than the sixth compressed oxidant flow rate, wherein the
substantially stoichiometric ratio is not maintained and fuel lean
combustion is achieved, producing a seventh mechanical power that
is less than the sixth mechanical power and producing a high oxygen
content product stream comprising a high oxygen content product
emissions level and a third heat release from the second at least
one oxidation catalyst unit resulting in a temperature of the
recirculated low oxygen content gas stream downstream of the second
at least one oxidation catalyst unit that is within a target
range.
[0346] Embodiment 229. The method of any preceding embodiment,
comprising: reducing fuel stream flow rate to an eighth stream flow
rate that is less than the first fuel stream flow rate and reducing
the first portion of the compressed oxidant stream flow rate to an
eighth compressed oxidant flow rate that is less than the first
compressed oxidant flow rate, wherein the substantially
stoichiometric ratio is maintained, producing an eighth mechanical
power that is less than the first mechanical power and producing a
low oxygen content product stream comprising an eighth low oxygen
content product emissions level that is within a target range and a
fourth heat release from the first at least one oxidation catalyst
unit resulting in a temperature of the low oxygen content product
stream downstream of the first at least one oxidation catalyst unit
that is within a target range; reducing fuel stream flow rate to a
ninth fuel stream flow rate that is less than the eighth fuel
stream flow rate and reducing the first portion of the compressed
oxidant stream flow rate to a ninth compressed oxidant flow rate
that is less than the eighth compressed oxidant flow rate, wherein
the substantially stoichiometric ratio is maintained, producing a
ninth mechanical power that is less than the eighth mechanical
power and producing a low oxygen content product stream comprising
a ninth low oxygen content product emissions level that is within a
target range and a fifth heat release from the first at least one
oxidation catalyst unit resulting in a temperature of the low
oxygen content product stream downstream of the first at least one
oxidation catalyst unit that is at the limit of a target range;
reducing fuel stream flow rate to a tenth fuel stream flow rate
that is less than the ninth fuel stream flow rate and reducing the
first portion of the compressed oxidant stream flow rate to a tenth
compressed oxidant flow rate that is less than the ninth compressed
oxidant flow rate, wherein the substantially stoichiometric ratio
is not maintained and fuel lean combustion is achieved, producing a
tenth mechanical power that is less than the ninth mechanical power
and producing a high oxygen content product stream comprising a
high oxygen content product emissions level and a sixth heat
release from the first at least one oxidation catalyst unit
resulting in a temperature of the high oxygen content product
stream downstream of the first at least one oxidation catalyst unit
that is within a target range.
[0347] Embodiment 230. The method of any preceding embodiment,
comprising a first at least one nitrogen oxide reduction catalyst
unit as part of the first at least one oxidation catalyst unit.
[0348] Embodiment 231. The method of any preceding embodiment,
comprising a second at least one nitrogen oxide reduction catalyst
unit as part of the second at least one oxidation catalyst
unit.
[0349] Embodiment 232. The method of any preceding embodiment,
comprising at least one of an inertial separator, coalescing filter
and a water impermeable filter downstream of the heat exchanger and
improving the effectiveness of removing the condensed water.
[0350] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they have structural elements that do not differ
from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal language of the claims.
* * * * *