U.S. patent application number 14/389294 was filed with the patent office on 2015-03-19 for turbomachine combustor assembly.
The applicant listed for this patent is Ilya Aleksandrovich Slobodyanskiy, Alexander Nikolay Sokolov, Dmitry Vladlenovich Tretyakov. Invention is credited to Ilya Aleksandrovich Slobodyanskiy, Alexander Nikolay Sokolov, Dmitry Vladlenovich Tretyakov.
Application Number | 20150075171 14/389294 |
Document ID | / |
Family ID | 47116252 |
Filed Date | 2015-03-19 |
United States Patent
Application |
20150075171 |
Kind Code |
A1 |
Sokolov; Alexander Nikolay ;
et al. |
March 19, 2015 |
TURBOMACHINE COMBUSTOR ASSEMBLY
Abstract
A turbomachine combustor assembly includes a combustor body, and
a combustor liner arranged within the combustor body. The combustor
liner defines a combustion chamber having a head end and a
discharge end. A plurality of combustor nozzles are arranged in an
annular array at the head end of the combustion chamber, and a
fluid delivery nozzle is arranged substantially centrally within
the annular array at the head end of the combustion chamber. The
fluid delivery nozzle includes a first end portion that extends to
a second end portion through a wall portion. The wall portion
includes at least one combustion chamber outlet. The fluid delivery
nozzle is configured to deliver a non-combustible fluid into the at
least one of the plurality of combustor nozzles and the combustion
chamber.
Inventors: |
Sokolov; Alexander Nikolay;
(Moscow, RU) ; Tretyakov; Dmitry Vladlenovich;
(Moscow, RU) ; Slobodyanskiy; Ilya Aleksandrovich;
(Greenville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Sokolov; Alexander Nikolay
Tretyakov; Dmitry Vladlenovich
Slobodyanskiy; Ilya Aleksandrovich |
Moscow
Moscow
Greenville |
SC |
RU
RU
US |
|
|
Family ID: |
47116252 |
Appl. No.: |
14/389294 |
Filed: |
March 29, 2012 |
PCT Filed: |
March 29, 2012 |
PCT NO: |
PCT/RU2012/000232 |
371 Date: |
September 29, 2014 |
Current U.S.
Class: |
60/772 ;
60/755 |
Current CPC
Class: |
F02C 7/18 20130101; F23C
9/08 20130101; F02C 3/04 20130101; F23C 2900/06041 20130101; F23C
7/02 20130101; F23R 2900/03041 20130101; F23R 3/283 20130101; F05D
2240/35 20130101; F23R 3/04 20130101; F23R 3/002 20130101; F23R
3/286 20130101 |
Class at
Publication: |
60/772 ;
60/755 |
International
Class: |
F23R 3/04 20060101
F23R003/04; F23R 3/00 20060101 F23R003/00 |
Claims
1. A turbomachine combustor assembly comprising: a combustor body;
a combustor liner arranged within the combustor body, the combustor
liner defining a combustion chamber having a head end and a
discharge end; a plurality of combustor nozzles arranged in an
annular array at the head end of the combustion chamber; a fluid
delivery nozzle arranged substantially centrally within the annular
array at the head end of the combustion chamber, the fluid delivery
nozzle including a first end portion that extends to a second end
portion through a wall portion, the wall portion including at least
one combustion chamber outlet, the fluid delivery nozzle being
configured to deliver a non-combustible fluid into the at least one
of the plurality of combustor nozzles.
2. The turbomachine combustor according to claim 1, wherein wall
portion includes a plurality of combustor nozzle outlets fluidly
connected to the plurality of combustor nozzles.
3. The turbomachine combustor assembly according to claim 2,
wherein one of the plurality of combustor nozzle outlets is fluidly
connected to two adjacent ones of the plurality of combustor
nozzles.
4. The turbomachine combustor assembly according to claim 1,
wherein the at least one combustion chamber outlet includes a first
combustion chamber outlet formed in the second end portion and a
second combustion chamber outlet formed in the wall portion
adjacent the second end portion.
5. The turbomachine combustor assembly according to claim 4,
wherein the first combustion chamber outlet of the fluid delivery
nozzle comprises an effusion plate provided at the second end
portion, the effusion plate having a plurality of openings that
partially obstruct flow passing from the fluid delivery nozzle into
the combustion chamber.
6. The turbomachine assembly according to claim 5, wherein the
second combustion chamber outlet includes a plurality of openings
formed in the wall portion at the second end portion.
7. The turbomachine assembly according to claim 6, wherein the
plurality of openings extend circumferentially about the wall
portion at the second end portion.
8. The turbomachine combustor assembly according to claim 1,
further comprising: at least one additional non-combustible fluid
outlet formed in the combustor liner adjacent the head end of the
combustion chamber, the at least one additional non-combustible
fluid outlet being configured and disposed to deliver additional
non-combustible fluid toward the plurality of combustor
nozzles.
9. The turbomachine combustor assembly according to claim 8,
wherein the additional non-combustible fluid includes one of an
exhaust gas and an inert gas.
10. The turbomachine combustor assembly according to claim 1,
wherein the non-combustible fluid is air.
11. A method of introducing a non-combustible fluid into a
turbomachine combustor, the method comprising: delivering a
non-combustible fluid into a fluid delivery nozzle extending into a
combustion chamber of the turbomachine combustor; passing a first
portion of the non-combustible fluid radially outward from the
fluid delivery nozzle into at least one of a plurality of combustor
nozzles arrayed about the fluid delivery nozzle; and passing a
second portion of the non-combustible fluid into the combustion
chamber through a combustion chamber outlet formed at an end of the
fluid delivery nozzle.
12. The method of claim 11, wherein passing the first portion of
the non-combustible fluid into at least one of the plurality of
combustor nozzles includes passing the first portion of the
non-combustible fluid through a combustor nozzle outlet formed in a
wall of the fluid delivery nozzle into two adjacent ones of the
plurality of combustor nozzles.
13. The method of claim 11, wherein passing the first portion of
the non-combustible fluid into at least one of the plurality of
combustor nozzles includes passing the first portion of the
non-combustible fluid into a first combustor nozzle creating a flow
about the first combustor nozzle in a first direction and into a
second combustor nozzle creating a flow about the second combustor
nozzle in a second direction that is opposite to the first
direction.
14. The method of claim 11, further comprising: passing a third
portion of the non-combustible fluid through another combustion
chamber outlet formed at the end of the fluid delivery nozzle, the
second portion of the non-combustible fluid passing radially from
the fluid delivery nozzle into the combustion chamber and the third
portion of the non-combustible fluid passing axially from the fluid
delivery nozzle into the combustion chamber.
15. The method of claim 11, further comprising: passing an
additional non-combustible fluid through a liner of the
turbomachine combustor toward the fluid delivery nozzle.
16. The method of claim 15, wherein passing the additional
non-combustible fluid toward the fluid delivery nozzle includes
passing one of an exhaust gas and an inert gas between adjacent
ones of the plurality of combustor nozzles.
17. A turbomachine comprising: a compressor portion; a turbine
portion mechanically linked to the compressor portion; and a
combustor assembly fluidly connected to the compressor portion and
the turbine portion, the combustor assembly comprising: a combustor
body; a combustor liner arranged within the combustor body, the
combustor liner defining a combustion chamber having a head end and
a discharge end; a plurality of combustor nozzles arranged in an
annular array at the head end of the combustion chamber; a fluid
delivery nozzle arranged substantially centrally within the annular
array at the head end of the combustion chamber, the fluid delivery
nozzle including a first end portion that extends to a second end
portion through a wall portion including a plurality of combustor
nozzle outlets fluidly connected to two adjacent ones of the
plurality of combustor nozzles, the wall portion including a first
combustion chamber outlet formed in the second end portion and a
second combustion chamber outlet formed in the wall portion
adjacent the second end portion; and at least one additional
non-combustible fluid outlet formed in the liner adjacent the head
end of the combustion chamber, the at least one additional
non-combustible fluid outlet being configured and disposed to
deliver a non-combustible fluid flow between adjacent ones of the
plurality of combustor nozzles.
18. The turbomachine according to claim 17, wherein the first
combustion chamber outlet of the fluid delivery nozzle comprises an
effusion plate provided at the second end portion, the effusion
plate having a plurality of openings that partially obstruct flow
passing from the fluid delivery nozzle into the combustion
chamber.
19. The turbomachine according to claim 18, wherein the second
combustion chamber outlet includes a plurality of openings formed
in the wall portion at the second end portion.
20. The turbomachine according to claim 19, wherein the plurality
of openings extend circumferentially about the wall portion at the
second end portion.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to the art of
turbomachines and, more particularly, to a turbomachine combustor
assembly.
[0002] Many turbomachines include a compressor portion linked to a
turbine portion through a common compressor/turbine shaft or rotor
and a combustor assembly. The compressor portion guides a
compressed airflow through a number of sequential stages toward the
combustor assembly. In the combustor assembly, the compressed
airflow mixes with a fuel to form a combustible mixture. The
combustible mixture is combusted in the combustor assembly to form
hot gases. The hot gases are guided to the turbine portion through
a transition piece. The hot gases expand through the turbine
portion creating work that is output, for example, to power a
generator, a pump, or to provide power to a vehicle. In addition to
providing compressed air for combustion, a portion of the
compressed airflow is passed through the turbine portion for
cooling purposes.
[0003] The combustor assembly includes a linier portion that
defines a combustion chamber. The combustible mixture is combusted
in the combustion chamber to form the hot gases. Over time, the
liner begins to erode due to exposure to the hot gases. Often
times, the erosion begins in high temperature zones located
adjacent outlet portions of combustor nozzles. The erosion will
have a negative impact on combustor operational life requiring
costly and periodic maintenance and replacement in order to
maintain turbomachine operation.
BRIEF DESCRIPTION OF THE INVENTION
[0004] According to one aspect of the exemplary embodiment, a
turbomachine combustor assembly includes a combustor body, and a
combustor liner arranged within the combustor body. The combustor
liner defines a combustion chamber having a head end and a
discharge end. A plurality of combustor nozzles are arranged in an
annular array at the head end of combustion chamber, and a fluid
delivery nozzle is arranged substantially centrally within the
annular array at the head end of the combustion chamber. The fluid
delivery nozzle includes a first end portion that extends to a
second end portion through a wall portion. The wall portion
includes at least one combustion chamber outlet. The fluid delivery
nozzle is configured to deliver a non-combustible fluid into the at
least one of the plurality of combustor nozzles.
[0005] According to another aspect of the exemplary embodiment, a
method of introducing a non-combustible fluid into a turbomachine
combustor includes delivering a non-combustible fluid into a fluid
delivery nozzle extending into a combustion chamber of the
turbomachine combustor, passing a first portion of the
non-combustible fluid into at least one of a plurality of combustor
nozzles arrayed about the fluid delivery nozzle, and passing a
second portion of the non-combustible fluid into the combustion
chamber through a combustion chamber outlet formed at an end of the
fluid delivery nozzle.
[0006] According to yet another aspect of the exemplary embodiment,
a turbomachine includes a compressor portion, a turbine portion
mechanically linked to the compressor portion, and a combustor
assembly fluidly connected to the compressor portion and the
turbine portion. The combustor assembly includes a combustor body,
and a combustor liner arranged within the combustor body. The
combustor liner defines a combustion chamber having a head end and
a discharge end. A plurality of combustor nozzles are arranged in
an annular array at the head end of combustion chamber, and a fluid
delivery nozzle arranged substantially centrally within the annular
array at the head end of the combustion chamber. The fluid delivery
nozzle includes a first end portion that extends to a second end
portion through a wall portion that includes a plurality of
combustor nozzle outlets fluidly connected to two adjacent ones of
the plurality of combustor nozzles. The wall portion includes a
first combustion chamber outlet formed in the second end portion
and a second combustion chamber outlet formed in the wall portion
adjacent the second end portion. At least one additional
non-combustible fluid outlet formed in the liner adjacent the head
end of the combustion chamber, the at least one additional
non-combustible fluid outlet is configured and disposed to deliver
a non-combustible fluid flow between adjacent ones of the plurality
of combustor nozzles
[0007] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF DRAWINGS
[0008] 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:
[0009] FIG. 1 is a schematic view of a turbomachine including a
combustor assembly in accordance with an exemplary embodiment;
[0010] FIG. 2 is a partial cross-sectional view of the combustor
assembly in accordance with the exemplary embodiment;
[0011] FIG. 3 is an end view of the combustor assembly of FIG. 2;
and
[0012] FIG. 4 is a detail view of a fluid delivery nozzle of the
combustor assembly of the exemplary embodiment.
[0013] 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
[0014] With reference to FIGS. 1 and 2, a turbomachine constructed
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. A combustor assembly 8 is fluidly
connected to compressor portion 4 and turbine portion 6. Combustor
assembly 8 is formed from a plurality of circumferentially spaced
combustors, one of which is indicated at 10. Of course it should be
understood that combustor assembly 8 could include other
arrangements of combustors. Compressor portion 4 is also linked to
turbine portion 6 through a common compressor/turbine shaft 12.
With this arrangement, compressor portion 4 delivers compressed air
to combustor assembly 8. The compressed air mixes with a
combustible fluid or fuel to form a combustible mixture. The
combustible mixture is combusted in combustor 10 to form products
of combustion or hot gases that are delivered to turbine portion 6
through a transition piece 14. The hot gases expand through turbine
portion 6 along a gas path (not separately labeled) to power, for
example, a generator, a pump, a vehicle or the like (also not
shown).
[0015] In accordance with an exemplary embodiment, combustor 10
includes a combustor body 20 within which is arranged a combustor
liner 24. Combustor liner 24 is spaced from combustor body 20 so as
to define a passage 26. Combustor liner 24 defines a combustion
chamber 30 having a first or head end 32 provided with a combustor
cap 34 and a second or discharge end 37 that is fluidly coupled to
transition piece 14. Combustor 10 includes a plurality of combustor
nozzles 44-49 (FIG. 3) arranged at head end 32. Combustor nozzles
44-49 are arranged in an annular array having a central region (not
separately labeled).
[0016] In the exemplary embodiment shown, combustor nozzle 44
includes an outer nozzle portion 52 that surrounds a central
discharge portion 53. Outer nozzle portion 52 is spaced from
central discharge portion 53 to form a fluid cavity 55. As will be
discussed more fully below, fluid cavity 55 receives a
non-combustible fluid such as air, steam, and/or an inert gas. The
non-combustible fluid mixes with a combustible fluid received
through a fuel inlet 56 that extends through combustor cap 34. The
combustible fluid passes through central discharge portion 53 and
mixes with the non-combustible fluid to form a combustible mixture.
The non-combustible fluid also provides cooling to combustor nozzle
44. In a manner similar to that described above, combustion nozzle
45 includes an outer nozzle portion 57, a central discharge portion
58 and a fluid cavity 60; combustor nozzle 46 includes an outer
nozzle portion 62, a central discharge portion 63 and a fluid
cavity 65; combustor nozzle 47 includes an outer nozzle portion 68,
a central discharge portion 69 and a fluid cavity 71; combustor
nozzle 48 includes an outer nozzle portion 73, a central discharge
portion 74 and a fluid cavity 76; and combustor nozzle 49 includes
an outer nozzle portion 78, a central discharge portion 79, and a
fluid cavity 80.
[0017] In further accordance with the exemplary embodiment,
combustor 10 includes a fluid delivery nozzle 90 arranged at head
end 32 and positioned within the central region (not separately
labeled) of combustor nozzles 44-49. Fluid delivery nozzle 90 is
fluidly connected to a non-combustible fluid inlet 92 and includes
a nozzle body 94 having a first end portion 98 that extends to a
second end portion 99 through a wall portion 100. Fluid delivery
nozzle 90 includes a plurality of combustor nozzle outlets, one of
which is indicated at 110, formed in wall portion 100. Fluid
delivery nozzle 90 also includes a first plurality of combustion
chamber outlets, one of which is indicated at 113, a second
plurality of combustion chamber outlets, one of which is indicated
at 115, and a third plurality of combustion chamber outlets 117
provided in wall potion 100. First plurality of combustion chamber
outlets 113 take the form of openings (not separately labeled)
formed in wall portion 100. While shown in a single row that
extends about nozzle body 94, the number or rows and size of the
first plurality of combustion chamber outlets 113 may vary. Second
plurality of combustion chamber outlets 115 takes the form of a
mini effusion plate 120 having a plurality of openings 122. Third
plurality of combustion chamber outlets 117 take the form of
openings 125 formed in wall portion 100 between combustor nozzle
outlets 110 and first combustion chamber outlets 113. Openings 125
are formed at a pair of flow re-direction elements, one of which is
indicated at 128 provided on an outer surface (not separately
labeled) of wall portion 100.
[0018] With this arrangement, a combustible fluid or fuel is passed
through fuel inlet 56 toward combustor nozzles 44-49. The fuel
passes from each central discharge portion 53, 58, 63, 69, and 74.
At generally the same time, a non-combustible fluid or air is
passed through non-combustible fluid inlet 92 toward fluid delivery
nozzle 90. The non-combustible fluid flows along nozzle body 94 and
passes into each fluid cavity 55, 60, 65, 71, and 76 through
combustor nozzle outlets 110. More specifically, combustor nozzle
outlets 110 are configured to deliver the non-combustible fluid
into two adjacent ones of combustor nozzles 44-49. With this
arrangement, the non-combustible fluid enters each fluid cavity 55,
60, 65, 71, and 76 in a particular orientation. For example, the
non-combustible fluid entering fluid cavity 55 may flow with a
counter-clockwise swirl and non-combustible fluid may enter fluid
cavity 60 with a clockwise swirl such as shown in FIG. 3. Thus,
swirls in adjacent nozzles flow in opposite directions. The
non-combustible fluid mixes with the combustible fluid and passes
from each combustor nozzle 44-49 as a combustible mixture that is
combusted within combustion chamber 30 to form hot gases. The hot
gases flow from combustor 10 into transition piece 14 and on toward
a first stage of turbine portion 6.
[0019] Additionally, a second portion of the non-combustible fluid
entering fluid nozzle 90 passes through first combustion chamber
outlets 113, a third portion of the non-combustible fluid passes
through second combustion chamber outlets 115, and a fourth portion
of the non-combustible fluid passes through third combustion
chamber outlets 117. The second portion of non-combustible fluid
passing from first combustion chamber outlets 113 flows radially
from fluid nozzle 90 into combustion chamber 30 to mix with the
combustible mixture to aid in more complete combustion. The third
portion of fluid passes through second combustion chamber outlets
115 axially into combustion chamber 30 and provides cooling to mini
effusion plate 120. The presence of mini-effusion plate 120 creates
a flow restriction that establishes a desired pressure within fluid
nozzle 90. Finally, the fourth portion of the non-combustible fluid
passes through third combustion chamber outlets 117 and is
re-directed by flow re-direction members 118 to form a film cooling
flow that flows over the outer surface (not separately labeled) of
wall member 100 for cooling purposes.
[0020] In addition to the combustible and non-combustible fluids
mixing and flowing from combustor nozzles 44-49 and fluid nozzle
90, combustor 10 includes an additional non-combustible fluid
outlets 134 134 formed in combustor liner 24. Additional
non-combustible fluid outlets 134 guide another non-combustible
fluid, such as exhaust gas (EG), steam, or another inert gas into
combustion chamber 30 to further enhance combustion and lead to
reduced emissions. Additional non-combustible fluid outlets 134
direct the additional non-combustible fluid radially inward toward
fluid delivery nozzle 90. More specifically, additional
non-combustible fluid outlets 134 are positioned to guide the
additional non-combustible fluid between adjacent ones of combustor
nozzles 44-49 to mix with and combust with the combustible mixture.
The introduction of the additional non-combustible fluid provides
cooling to inner surfaces (not separately labeled) of the combustor
liner and further leads to lower emissions from turbomachine 2.
Cooling the inner surface of the combustion liner leads to an
increase in service life of the combustion liner and, by extension,
the combustor. That is, by increasing a service life of the
combustor, costly maintenance procedures are reduced along with a
downtime of the turbomachine. In addition, mixing of combustible
and non-combustible fluid provided by the fluid delivery nozzle
along with the additional non-combustible fluids leads to more
complete burning of various substances such as CO and the like that
lead to lower emissions from gas turbomachine 2.
[0021] 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.
* * * * *