U.S. patent application number 13/983878 was filed with the patent office on 2014-08-28 for turbomachine combustor assembly and method of operating a turbomachine.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is Ilya Aleksandrovich Slobodyanskiy, Sergey Aleksandrovich Stryapunin, Dmitry Vladlenovich Tretyakov. Invention is credited to Ilya Aleksandrovich Slobodyanskiy, Sergey Aleksandrovich Stryapunin, Dmitry Vladlenovich Tretyakov.
Application Number | 20140238034 13/983878 |
Document ID | / |
Family ID | 46506614 |
Filed Date | 2014-08-28 |
United States Patent
Application |
20140238034 |
Kind Code |
A1 |
Slobodyanskiy; Ilya Aleksandrovich
; et al. |
August 28, 2014 |
TURBOMACHINE COMBUSTOR ASSEMBLY AND METHOD OF OPERATING A
TURBOMACHINE
Abstract
A turbomachine combustor assembly includes a combustor body
having a combustor outlet, and a combustion liner arranged within
the combustor body. The combustion liner defines a combustion
chamber. An injection nozzle is arranged within the combustor body
upstream from the combustion chamber. The injection nozzle is
configured and disposed to deliver a first fluid toward the
combustion chamber. A fluid module is mounted to the combustor body
downstream from the combustion chamber. The fluid module includes a
fluid module body that defines a fluid zone, a first injector
member mounted to the fluid module body and configured to deliver a
second fluid into the fluid zone at a first orientation, and a
second injector member mounted to the fluid module body and
configured to deliver a third fluid into the fluid zone at a second
orientation that is distinct from the first orientation.
Inventors: |
Slobodyanskiy; Ilya
Aleksandrovich; (Greenville, SC) ; Stryapunin; Sergey
Aleksandrovich; (Moscow, RU) ; Tretyakov; Dmitry
Vladlenovich; (Moscow, RU) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Slobodyanskiy; Ilya Aleksandrovich
Stryapunin; Sergey Aleksandrovich
Tretyakov; Dmitry Vladlenovich |
Greenville
Moscow
Moscow |
SC |
US
RU
RU |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
46506614 |
Appl. No.: |
13/983878 |
Filed: |
November 17, 2011 |
PCT Filed: |
November 17, 2011 |
PCT NO: |
PCT/RU2011/000908 |
371 Date: |
August 6, 2013 |
Current U.S.
Class: |
60/772 ;
60/752 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 3/346 20130101 |
Class at
Publication: |
60/772 ;
60/752 |
International
Class: |
F23R 3/00 20060101
F23R003/00 |
Claims
1. A turbomachine combustor assembly comprising: a combustor body
having a combustor outlet; a combustion liner arranged within the
combustor body, the combustion liner defining a combustion chamber;
an injection nozzle arranged within the combustor body upstream
from the combustion chamber, the injection nozzle being configured
and disposed to deliver a first fluid toward the combustion
chamber; and a fluid module mounted to the combustor body
downstream from the combustion chamber, the fluid module including
a fluid module body that defines a fluid zone, a first injector
member mounted to the fluid module body and configured to deliver a
second fluid into the fluid zone at a first orientation, and a
second injector member mounted to the fluid module body and
configured to deliver a third fluid into the fluid zone at a second
orientation that is distinct from the first orientation.
2. The turbomachine combustor assembly according to claim 1,
wherein the injection nozzle is configured and disposed to deliver
an axial stream of the first fluid toward the combustion
chamber
3. The turbomachine combustor assembly according to claim 2,
wherein the first injector member is configured to deliver a first
radial stream of the second fluid into the fluid zone at the first
orientation, and the second injector member is configured to
deliver a second radial stream of the third fluid into the fluid
zone at the second orientation.
4. The turbomachine combustor assembly according to claim 3,
wherein the first orientation is substantially perpendicular to the
fluid module body and the second orientation is angled downstream
of the first orientation.
5. The turbomachine combustor assembly according to claim 1,
wherein the first injector member includes a first plurality of
injector members arranged in an annular array about the fluid
module body and the second injector member includes a second
plurality of injector members arranged in an annular array about
the fluid module body.
6. The turbomachine combustor assembly according to claim 5,
wherein the second plurality of injector members is arranged
downstream relative to the first plurality of injector members.
7. The turbomachine combustor assembly according to claim 1,
wherein the injection nozzle is configured and disposed to
establish a first fluid zone, the first injector member is
configured and disposed to establish a second fluid zone downstream
from the first fluid zone, and the second injector member is
configured to establish a third fluid zone downstream from the
second fluid zone.
8. A method of operating a turbomachine comprising: introducing a
first fluid into a combustor assembly to establish a first fluid
zone; introducing a second fluid into the combustor assembly to
establish a second fluid zone down stream of the first fluid zone;
introducing a third fluid into the combustor assembly to establish
a third fluid zone downstream of the second fluid zone; and
combusting one or more of the first, second and third fluids to
produce a hot gas stream to establish a first operating mode of the
turbomachine.
9. The method of claim 8, wherein introducing the first fluid
includes guiding a stream of the first fluid along a longitudinal
axis of the combustor assembly.
10. The method of claim 9, wherein introducing the second fluid
includes injecting a stream of the second fluid along a first
radial axis of the combustor assembly.
11. The method of claim 10, wherein introducing the third fluid
includes injecting a stream of the third fluid along a second
radial axis of the combustor assembly, the second radial axis being
angled relative to the first radial axis.
12. The method of claim 8, further comprising: ceasing introduction
of the third fluid establishing a second operating mode of the
turbomachine.
13. The method of claim 12, wherein establishing the second
operating mode includes operating the turbomachine at about 40% to
about 70% of the first operating mode.
14. The method of claim 12, further comprising: ceasing
introduction of the second fluid establishing a third operating
mode of the turbomachine.
15. The method of claim 14, wherein establishing the third
operating mode includes operating the turbomachine at about 20% to
about 40% of the first operating mode.
16. A turbomachine comprising: a compressor portion; a turbine
portion operatively connected to the turbine portion; and a
combustor assembly fluidly connected to the compressor portion and
the turbine portion, the combustor assembly comprising: a combustor
body; a combustion liner arranged within the combustor body, the
combustion liner defining a combustion chamber; an injection nozzle
arranged within the combustor body upstream from the combustion
chamber, the injection nozzle being configured and disposed to
introduce a first fluid toward the combustion chamber; and a fluid
module mounted to the combustor body downstream from the combustion
chamber, the fluid module including a fluid module body that
defines a fluid zone, a first injector member mounted to the fluid
module body and configured to deliver a second fluid into the fluid
zone at a first orientation, and a second injector member mounted
to the fluid module body and configured to deliver a third fluid
into the fluid zone at a second orientation that is distinct from
the first orientation.
17. The turbomachine according to claim 16, wherein the injection
nozzle is configured and disposed to deliver an axial stream of the
first fluid toward the combustion chamber.
18. The turbomachine according to claim 16, wherein the first
injector member is configured to deliver a radial stream of the
second fluid into the fluid zone, and the second injector member is
configured to deliver a radial stream of the third fluid into the
fluid zone.
19. The turbomachine according to claim 16, wherein the injection
nozzle is configured and disposed to establish a first fluid zone,
the first injector member is configured and disposed to establish a
second fluid zone down stream from the first fluid zone, and the
second injector member is configured to establish a third fluid
zone downstream from the second fluid zone.
20. The turbomachine according to claim 18, further comprising: a
transition piece fluidly connecting the combustor assembly and the
turbine portion, at least a portion of one the third fluid zone
residing in the transition piece.
Description
CROSS REFERENCE TO RELATED APPLICATION
[0001] This is a National Stage Application claiming priority to
PCT Application No. PCT/RU2011/000908 filed Nov. 9, 2011, the
entire contents of which are incorporated herein by reference.
BACKGROUND OF THE INVENTION
[0002] The subject matter disclosed herein relates to the art of
turbomachines and, more particularly, to a turbomachine combustor
assembly.
[0003] In general, gas turbomachines combust a fuel/air mixture
that releases heat energy to form a high temperature gas stream.
The high temperature gas stream is channeled to a turbine portion
via a hot gas path. The turbine portion converts thermal energy
from the high temperature gas stream to mechanical energy that
rotates a turbine shaft. The turbomachine may be used in a variety
of applications, such as for providing power to a pump, an
electrical generator, or aircraft.
[0004] Turbomachine efficiency increases as combustion gas stream
temperatures increase. Unfortunately, higher gas stream
temperatures produce higher levels of nitrogen oxide (NOx), an
emission that is subject to both federal and state regulation.
Therefore, there exists a careful balancing act between operating
gas turbomachines in an efficient range, while also ensuring that
the output of NOx remains below federal and state mandated levels.
One method of achieving low NOx levels is to ensure good mixing of
fuel and air prior to combustion and providing an environment that
leads to more complete combustion of the fuel/air mixture.
BRIEF DESCRIPTION OF THE INVENTION
[0005] According to one aspect of the exemplary embodiment, a
turbomachine combustor assembly includes a combustor body having a
combustor outlet, and a combustion liner arranged within the
combustor body. The combustion liner defines a combustion chamber.
An injection nozzle is arranged within the combustor body upstream
from the combustion chamber. The injection nozzle is configured and
disposed to deliver a first fluid toward the combustion chamber. A
fluid module is mounted to the combustor body downstream from the
combustion chamber. The fluid module includes a fluid module body
that defines a fluid zone, a first injector member mounted to the
fluid module body and configured to deliver a second fluid into the
fluid zone at a first orientation, and a second injector member
mounted to the fluid module body and configured to deliver a third
fluid into the fluid zone at a second orientation that is distinct
from the first orientation.
[0006] According to another aspect of the exemplary embodiment, a
method of operating a turbomachine includes introducing a first
fluid into a combustor assembly to establish a first fluid zone,
introducing a second fluid into the combustor assembly to establish
a second flame zone down stream of the first fluid zone,
introducing a third fluid into the combustor assembly to establish
a third fluid zone downstream of the second fluid zone, and
combusting one or more of the first, second and third fluids to
produce a hot gas stream to establish a first operating mode of the
turbomachine.
[0007] According to yet another aspect of the exemplary embodiment,
a turbomachine includes a compressor portion, a turbine portion
operatively connected to the turbine portion, and a combustor
assembly fluidly connected to the compressor portion and the
turbine portion. The combustor assembly includes a combustor body,
and a combustion liner arranged within the combustor body. The
combustion liner defines a combustion chamber. An injection nozzle
is arranged within the combustor body upstream from the combustion
chamber. The injection nozzle is configured and disposed to
introduce a first fluid toward the combustion chamber. A fluid
module is mounted to the combustor body downstream from the
combustion chamber. The fluid module includes a fluid module body
that defines a fluid zone, a first injector member mounted to the
fluid module body and configured to deliver a second fluid into the
fluid zone at a first orientation, and a second injector member
mounted to the fluid module body and configured to deliver a third
fluid into the fluid zone at a second orientation that is distinct
from the first orientation.
[0008] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF THE DRAWING
[0009] The subject matter, which is regarded as the invention, is
particularly pointed out and distinctly claimed in the claims at
the conclusion of the specification. The foregoing and other
features, and advantages of the invention are apparent from the
following detailed description taken in conjunction with the
accompanying drawings in which:
[0010] FIG. 1 is a schematic diagram of a turbomachine including a
combustor assembly having a fluid module in accordance with the
exemplary embodiment;
[0011] FIG. 2 is a partial perspective view of the combustor
assembly of FIG. 1;
[0012] FIG. 3 is a partial cross-sectional view of the combustor
assembly of FIG. 2;
[0013] FIG. 4 is a schematic partial cross-sectional view of the
fluid module in accordance with the exemplary embodiment;
[0014] FIG. 5 is a partial cross-sectional view of the combustor
assembly of FIG. 2 illustrating a first operating mode in which
fluid mixtures are introduced into first, second, and third fluid
zones;
[0015] FIG. 6 is a partial cross-sectional view of the combustor
assembly of FIG. 2 illustrating a second operating mode in which
fluid mixtures are introduced into the first and second fluid
zones; and
[0016] FIG. 7 is a partial cross-sectional view of the combustor
assembly of FIG. 2 illustrating a third operating mode in which a
fluid mixture is introduced into the first fluid zone.
[0017] The detailed description explains embodiments of the
invention, together with advantages and features, by way of example
with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0018] With reference to FIG. 1, a turbomachine in accordance with
an exemplary embodiment is indicated generally at 2. Turbomachine 2
includes a compressor portion 4 operatively connected to a turbine
portion 6. Turbomachine 2 also includes a combustor assembly 8 that
fluidly links compressor portion 4 and turbine portion 6. A common
compressor/turbine shaft 10 mechanically links compressor portion 4
and turbine portion 6. With this arrangement, compressed air is
passed into combustor assembly 8, mixed with fuel, and combusted to
form hot gases. The hot gases are channeled to turbine portion 6
which converts thermal energy from the hot gases into mechanical
rotational energy that is channeled to drive an external component
such as a generator, a pump or other mechanically or fluidly driven
mechanism.
[0019] As shown in FIGS. 2-3, combustor assembly 8 includes a
combustor body 20 having an outer surface 22 and an inner surface
24. A combustor liner 30 is arranged within combustor body 20.
Combustor liner 30 includes an outer surface portion 32 and an
inner surface portion 34. Outer surface portion 32 is spaced from
inner surface 24 of combustor body 20 to form a duct or passage 36.
Combustor body 20 is also shown to include an upstream portion 37
and a downstream portion 39 between which define a combustion
chamber 44. Combustor assembly 8 includes a plurality of injection
nozzles, one of which is indicated at 50, supported by combustor
body 20 and positioned at upstream portion 37 of combustor liner
30. Injection nozzle 50 injects a first fluid mixture 51 into
combustion chamber 44. The first fluid mixture passes along a
longitudinal axis of combustor assembly 8. The longitudinal axis
should be understood to describe an axis of combustor assembly that
extends between upstream portion 37 and downstream portion 39.
[0020] In accordance with the exemplary embodiment, combustor
assembly 8 includes a fluid module 60 mounted at downstream portion
39 of combustor body 20. Fluid module 60 includes a fluid module
body 62 that defines a fluid zone 64. Fluid module 60 also includes
an inlet section 67 and an outlet section 69. Outlet section 69
joins with a transition piece 75. Transition piece 75 includes a
duct 77 that delivers products of combustion to turbine portion 6.
As will be discussed more fully below, duct 77 defines a combustion
area 79.
[0021] In further accordance with the exemplary embodiment, fluid
module 60 includes a plurality of first injector members 84
arranged in an annular array upstream relative to an annular array
of a plurality of second injector members 86. The plurality of
first injector members 84 receives fuel via a first fluid supply
conduit 89 provided in combustor body 20. First fluid supply
conduit 89 includes a first fluid inlet 90 that is configured to
receive a first fluid. The first fluid could be a fuel, an inert
gas or other liquid or gaseous mixture. Similarly, the plurality of
second injector members receive a second fluid through a second
fluid supply conduit 92 provided on combustor body 20. Second fluid
supply conduit 92 includes a second fluid inlet 93 that is
configured to receive a second fluid. In a manner similar to that
described above, the second fluid could be fuel, an inert gas or
other liquid or gaseous mixture. At this point it should be
understood that the first and second fluids may be substantially
identical or may be distinct one from the other depending upon
desired operation parameters. In addition, each of the first and
second injector members 84 and 86 include corresponding first and
second third fluid inlets 96 and 97. Third fluid inlets may provide
air from compressor portion 4 to each of the first and second
injector members 84, 86 or some other liquid or gaseous mixture
that is mixed with corresponding ones of the first and second
fluids.
[0022] In still further accordance with the exemplary embodiment
illustrated in FIG. 4, each first injector member 84 includes a
first injector body 108 mounted to fluid module body 62 at a first
orientation. First injector body 108 includes a third fluid passage
110 that is fluidly coupled to third fluid inlet 96 and a first
fluid passage 112. First fluid passage 112 extends within third
fluid passage 110 and is fluidly coupled to first fluid supply
conduit 89. Each first injector member 84 is configured to
introduce a second fluid mixture 119 into combustion zone 64. More
specifically, each first injector member 84 is oriented to deliver
a stream of the second fluid mixture that may include the first
fluid and the third fluid along a radial axis into combustion zone
64. It should be understood that the term radial axis describes an
axis that is substantially perpendicular to the longitudinal axis
of the combustor assembly.
[0023] Each second injector member 86 includes a second injector
body 130 mounted to fluid module body 62. Second injector body 130
includes a second third fluid passage 132 that is fluidly coupled
to second third fluid inlet 97 and a second fluid passage 134.
Second fluid passage 134 extends within second third fluid passage
132 and is fluidly coupled to second fluid supply conduit 92. Each
second injector member 86 is configured to introduce a third fluid
mixture 141 toward combustion area 79. More specifically, each
second injector member 86 is oriented to deliver a mixture of the
second and third fluids along an axis that is angled relative to
the longitudinal axis and the radial axis. Each second injector
member 86 is configured to deliver a third fluid mixture stream 142
downstream from second fluid mixture 119. Of course it should be
understood that the particular angle can vary. Third fluid mixture
may include both the second and third fluids.
[0024] With this arrangement, combustor assembly 8 can be operated
in one of a plurality of modes depending upon a desired power
output. In accordance with one aspect of the exemplary embodiment,
combustor assembly 8 can be selectively operated in a first or base
load mode in which first fluid mixture 51 defines a first
combustible mixture and is combusted in a first fluid zone 154,
second fluid mixture 119 defines a second combustible mixture and
is combusted in a second fluid zone 157, and third fluid mixture
142 defines a third combustible mixture and is combusted in a third
fluid zone 160 such as shown in FIG. 5. The three fluid zones 154,
157, and 159 lead to more complete combustion and establish a
prolonged residence time of the fluid mixtures that leads to a more
uniform heat release that results in lower combustion dynamics. It
should be understood that the second mixture could include any air
and/or inert gas to promote more complete combustion of the first
and third mixtures.
[0025] Combustor assembly 8 can also be selectively operated in a
second or first off-peak mode such as when desired power output is
between about 40% and 70% of base load. In the second mode, the
third fluid mixture does not contain any combustibles and may
represent air or a mixture of inert gases. Alternatively, the third
fluid mixture may simply be discontinued. In any case, in the
second mode only the first and second fluid zones 154 and 157 are
active such as shown in FIG. 6. Combustor assembly 8 may also be
operated in a third mode such as when desired power output is
between about 20% and 40% of base load. In the third mode, only
first fluid zone 154 is active. The second and third fluid mixtures
do not contain combustibles and may represent air or an inert gas
mixture. Alternatively the second and third fluid mixtures may
simply be discontinued.
[0026] At this point, it should be understood that the combustor
assembly of the exemplary embodiment allows for the selective
introduction of fluid mixtures into various positions along a
combustion path. The fluid mixtures can all represent combustible
mixtures or can represent mixtures of air or other inert fluids.
Inert fluids can be introduced downstream from combustible fluids
or may be introduced upstream of combustible fluids to facilitate
more complete combustion. The introduction of inert fluids upstream
of a combustion event has been shown to reduce undesirable
emissions.
[0027] While the invention has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the invention is not limited to such
disclosed embodiments. Rather, the invention can be modified to
incorporate any number of variations, alterations, substitutions or
equivalent arrangements not heretofore described, but which are
commensurate with the spirit and scope of the invention.
Additionally, while various embodiments of the invention have been
described, it is to be understood that aspects of the invention may
include only some of the described embodiments. Accordingly, the
invention is not to be seen as limited by the foregoing
description, but is only limited by the scope of the appended
claims.
* * * * *