U.S. patent application number 13/273372 was filed with the patent office on 2013-04-18 for annular flow conditioning member for gas turbomachine combustor assembly.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is Mahesh Bathina, Madanmohan Manoharan. Invention is credited to Mahesh Bathina, Madanmohan Manoharan.
Application Number | 20130091848 13/273372 |
Document ID | / |
Family ID | 47080304 |
Filed Date | 2013-04-18 |
United States Patent
Application |
20130091848 |
Kind Code |
A1 |
Manoharan; Madanmohan ; et
al. |
April 18, 2013 |
ANNULAR FLOW CONDITIONING MEMBER FOR GAS TURBOMACHINE COMBUSTOR
ASSEMBLY
Abstract
A turbomachine combustor assembly includes a combustor body, a
combustor liner arranged within the combustor body and defining a
combustion chamber, a fluid passage defined between the combustor
body and the combustor liner, and an annular flow conditioning
member arranged in the fluid passage and extending about the
combustor liner.
Inventors: |
Manoharan; Madanmohan;
(Chennai, IN) ; Bathina; Mahesh; (Ongole,
IN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Manoharan; Madanmohan
Bathina; Mahesh |
Chennai
Ongole |
|
IN
IN |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
47080304 |
Appl. No.: |
13/273372 |
Filed: |
October 14, 2011 |
Current U.S.
Class: |
60/752 |
Current CPC
Class: |
F23R 3/286 20130101;
F23R 3/54 20130101 |
Class at
Publication: |
60/752 |
International
Class: |
F23R 3/42 20060101
F23R003/42 |
Claims
1. A turbomachine combustor assembly comprising: a combustor body;
a combustor liner arranged within the combustor body and defining a
combustion chamber; a fluid passage defined between the combustor
body and the combustor liner; and an annular flow conditioning
member arranged in the fluid passage and extending about the
combustor liner.
2. The turbomachine combustor assembly according to claim 1,
wherein the annular flow conditioning member includes an external
surface and an internal surface that defines an annular fuel
plenum.
3. The turbomachine combustor assembly according to claim 2,
wherein the external surface of the annular flow conditioning
member includes an aerodynamic profile.
4. The turbomachine combustor assembly according to claim 3,
wherein the aerodynamic profile defines an airfoil.
5. The turbomachine combustor assembly according to claim 2,
wherein the annular flow conditioning member includes a plurality
of openings extending through the external and internals surfaces,
the plurality of openings fluidly connecting the annular fuel
plenum and the fluid passage.
6. The turbomachine combustor assembly according to claim 2,
further comprising: a fuel delivery passage fluidly connected to
the annular fuel plenum.
7. The turbomachine combustor assembly according to claim 1,
further comprising: a support member extending between the
combustor body and the annular flow conditioning member.
8. The turbomachine combustor assembly according to claim 7,
further comprising: another between the combustor liner and the
annular flow conditioning member.
9. The turbomachine combustor assembly according to claim 1,
further comprising: another annular flow conditioning member
arranged in the fluid passage and extending about the combustor
liner.
10. The turbomachine combustor assembly according to claim 9,
wherein the another annular flow conditioning member extends about
the annular flow conditioning member.
11. The turbomachine combustor assembly according to claim 9,
wherein the another annular flow conditioning member is arranged
downstream relative to the annular flow conditioning member.
12. The turbomachine combustor assembly according to claim 11,
wherein the another annular flow conditioning member is arranged
substantially co-planar relative to the annular flow conditioning
member.
13. The turbomachine combustor assembly according to claim 11,
wherein the another annular flow conditioning member is axially
off-set relative to the annular flow conditioning member.
14. A gas turbomachine system comprising: a compressor portion; a
turbine portion operatively coupled to the compressor portion; and
a combustor assembly fluidly connecting the compressor portion and
the turbine portion, the combustor assembly comprising: a combustor
body; a combustor liner arranged within the combustor body and
defining a combustion chamber; a fluid passage defined between the
combustor body and the combustor liner; and an annular flow
conditioning member arranged in the fluid passage and extending
about the combustor liner.
15. The gas turbomachine system according to claim 14, wherein the
annular flow conditioning member includes an external surface that
defines an aerodynamic profile and an internal surface that defines
an annular fuel plenum.
16. The gas turbomachine system according to claim 14, further
comprising: another annular flow conditioning member arranged in
the fluid passage and extending about the combustor liner.
17. The gas turbomachine system according to claim 16, wherein the
another annular flow conditioning member extends about the annular
flow conditioning member.
18. The gas turbomachine system according to claim 16, wherein the
another annular flow conditioning member is arranged downstream
relative to the annular flow conditioning member.
19. The gas turbomachine system according to claim 18, wherein the
another annular flow conditioning member is arranged substantially
co-planar relative to the annular flow conditioning member.
20. The gas turbomachine system according to claim 18, wherein the
another annular flow conditioning member is axially off-set
relative to the annular flow conditioning member.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to the art of
turbomachines and, more particularly, to an annular flow
conditioning member for a gas turbomachine combustor assembly.
[0002] In general, gas turbine engines 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 via a hot
gas path. The turbine converts thermal energy from the high
temperature gas stream to mechanical energy that rotates a turbine
shaft. The turbine may be used in a variety of applications, such
as for providing power to a pump or an electrical generator.
[0003] Many gas turbines include an annular combustor within which
are formed the combustion gases that create the high temperature
gas stream. Other turbomachines employ a plurality of combustors
arranged in a can-annular array. In such a turbomachine, the
combustion gases are formed in each of the plurality of combustors,
combusted in a combustion chamber defined by a combustor body, and
delivered to the turbine through a transition piece. Often times,
compressor discharge air is passed into the combustor to cool
various surfaces and aid in forming the fuel/air mixture. In
certain arrangements, compressor discharge air is often channeled
along a combustor liner toward a venturi.
[0004] A portion of the compressor discharge air is directed onto
internal surfaces of the venturi for cooling. The compressor
discharge air passes from the venturi into a passage formed between
the combustor body and the combustor liner. In certain
arrangements, a plurality of turbulator members is arranged in the
passage. The turbulator members create flow vortices that enhance
heat transfer in the combustor body. The compressor discharge air
exits the passage into the combustion chamber to mix with the
combustion gases.
BRIEF DESCRIPTION OF THE INVENTION
[0005] According to one aspect of the exemplary embodiment, a
turbomachine combustor assembly includes a combustor body, a
combustor liner arranged within the combustor body and defining a
combustion chamber, a fluid passage defined between the combustor
body and the combustor liner, and an annular flow conditioning
member arranged in the fluid passage and extending about the
combustor liner.
[0006] According to another aspect of the exemplary embodiment, a
gas turbomachine system including a compressor portion, a turbine
portion operatively coupled to the compressor portion, and a
combustor assembly fluidly connecting the compressor portion and
the turbine portion. The combustor assembly includes a combustor
body, a combustor liner arranged within the combustor body and
defining a combustion chamber, a fluid passage defined between the
combustor body and the combustor liner, and an annular flow
conditioning member arranged in the fluid passage and extending
about the combustor liner.
[0007] 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
[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 diagram of a gas turbomachine system
including a combustor assembly having a flow conditioning member in
accordance with an exemplary embodiment;
[0010] FIG. 2 is a partial cross-sectional view of the combustor
assembly of FIG. 1 illustrating a flow conditioning member in
accordance with an exemplary embodiment;
[0011] FIG. 3 is a perspective view of a flow conditioning member
in accordance with an exemplary embodiment;
[0012] FIG. 4 is a partial cross-sectional view of the combustor
assembly of FIG. 2 illustrating the flow conditioning member in
accordance with an exemplary embodiment;
[0013] FIG. 5 is a partial cross-sectional view of the combustor
assembly of FIG. 1 illustrating first and second flow conditioning
members in accordance with an exemplary embodiment;
[0014] FIG. 6 is a partial cross-sectional view of the combustor
assembly of FIG. 1 illustrating first and second flow conditioning
members in accordance with another aspect of the exemplary
embodiment;
[0015] FIG. 7 is a partial cross-sectional view of the combustor
assembly of FIG. 1 illustrating first and second flow conditioning
members in accordance with yet another exemplary embodiment;
and
[0016] FIG. 8 is a partial cross-sectional view of the combustor
assembly of FIG. 1 illustrating first and second flow conditioning
members in accordance with still yet another exemplary
embodiment.
[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 constructed in
accordance with an exemplary embodiment is indicated generally at
2. Turbomachine 2 includes a compressor portion 4 and a turbine
portion 6. Compressor portion 4 includes a compressor housing 8 and
turbine portion 6 includes a turbine housing 10. Compressor portion
4 is linked to turbine portion 6 through a common
compressor/turbine shaft or rotor 16. Compressor portion 4 is also
linked to turbine portion 6 through a plurality of
circumferentially spaced combustor assemblies, one of which is
indicated at 20.
[0019] As best shown in FIG. 2, combustor assembly 20 includes a
combustor body 34 having a forward end 36 to which is mounted an
injector nozzle housing 37. Combustor body 34 includes an outer
surface 38 and an inner surface 39. In the exemplary embodiment
shown, combustor assembly 20 includes a combustor liner 43 arranged
within combustor body 34. Combustor liner 43 includes an inner
surface 44 and an outer surface 45. Outer surface 45 is spaced from
an inner surface 39 of combustor body 34 thereby forming a fluid
flow passage 46 that transmits compressor discharge air from
compressor portion 4 toward injector nozzle housing 37. Inner
surface 44 of combustor liner 43 defines a combustion chamber 48.
In further accordance with the exemplary embodiment shown,
combustor assembly 20 includes an annular flow conditioning member
60. As will become more fully evident below, flow conditioning
member 60 is arranged within fluid flow passage 46 and extends
about combustor liner 43.
[0020] Annular flow conditioning member 60 includes an external
surface 64 and an internal surface 66 that defines an annular fuel
plenum 70. External surface 64 of flow conditioning member 60
includes an aerodynamic profile 75 that defines an airfoil 77. As
best shown in FIG. 3, annular flow conditioning member 60 includes
a first airfoil surface 79 and a second airfoil surface 80. First
airfoil surface 79 includes a plurality of openings 82 and second
airfoil surface 80 includes a second plurality of openings 84.
Openings 82 and 84 extend into annular fuel plenum 70. With this
arrangement, fuel flowing into annular fuel plenum 70 exits through
first and second plurality of openings 82 and 84 to mix with air
flowing through fluid flow passage 46 prior to entering an
injection nozzle (not shown) and being combusted in combustion
chamber 48. The particular profile of annular flow conditioning
member 60 enhances air/fuel mixing. In addition, the positioning of
annular flow conditioning member 60 within fluid flow passage 46
leads to more consistent flow velocities particularly in axial and
tangential directions. Furthermore, by supporting annular flow
conditioning member 60 within fluid flow passage 46 flow
separations are reduced.
[0021] In further accordance with the exemplary embodiment, annular
flow conditioning member 60 is supported within fluid flow passage
46 by first and second support members 87 and 90. First support
member 87 extends between inner surface 39 of combustor body 34 and
first airfoil surface 79. Second support member 90 extends between
second airfoil surface 80 and combustor liner 43. The number and
location of support members 87 and 89 can vary. That is, while
shown with two support members 87 and 90, annular flow conditioning
member 60 could be supported within flow passage 46 through a
single support member that extends from combustor body 34 or
combustor liner 43. In addition to first and second support members
87 and 89, annular flow conditioning member 60 is coupled to a fuel
delivery passage 93 (FIG. 4). In accordance with one aspect of the
exemplary embodiment first and second support members 87 and 89 are
designed with an airfoil shape so as to reduce downstream flow
separation. Fuel delivery passage 93 fluidly couples annular fuel
plenum 70 and a source of fuel (not shown). Fuel delivery passage
93 may take on a variety of forms that include rigid and flexibly
connections.
[0022] Reference will now be made to FIG. 5, wherein like reference
numbers represent corresponding parts in the respective views, in
describing a combustor assembly 106 in accordance with another
aspect of the exemplary embodiment. Combustor assembly 106 includes
a first annular flow conditioning member 110 having a first annular
fuel plenum 111 and a second annular flow conditioning member 113
having a second annular fuel plenum 114. First annular flow
conditioning member 110 includes a first aerodynamic profile 117
that defines a first airfoil 118. Similarly, second annular flow
conditioning member 113 includes a second aerodynamic profile 121
that defines a second airfoil 122. In the exemplary aspect shown,
first annular flow conditioning member 110 extends about second
annular flow conditioning member 113 within fluid flow passage 46.
The number and radial location of annular flow conditioning members
110 and 113 can vary. The particular orientation of flow
conditioning members 110 and 113 allows for enhanced fuel/air
mixing while also leading to more consistent flow velocities and
reduced air/fuel separation within fluid flow passage 46.
[0023] Reference will now be made to FIG. 6, wherein like reference
numbers represent corresponding parts in the respective views, in
describing a combustor assembly 126 in accordance with another
aspect of the exemplary embodiment. Combustor assembly 126 includes
a first annular flow conditioning member 130 having a first annular
fuel plenum 131 and a second annular flow conditioning member 133
having a second annular fuel plenum 134. First annular flow
conditioning member 130 includes a first aerodynamic profile 137
that defines a first airfoil 138. Similarly, second annular flow
conditioning member 133 includes a second aerodynamic profile 141
that defines a second airfoil 142. In the exemplary aspect shown,
second annular flow conditioning member 133 is positioned
downstream from first annular flow conditioning member 130 within
fluid flow passage 46. The number and axial location of annular
flow conditioning members 130 and 133 can vary. In a manner similar
to that described above, the particular orientation of flow
conditioning members 133 and 130 allows for enhanced fuel/air
mixing while also leading to more consistent flow velocities and
reduced air/fuel separation within fluid flow passage 46.
[0024] Reference will now be made to FIG. 7, wherein like reference
numbers represent corresponding parts in the respective views, in
describing a combustor assembly 144 in accordance with another
aspect of the exemplary embodiment. Combustor assembly 144 includes
a first annular flow conditioning member 146 having a first annular
fuel plenum 147 and a second annular flow conditioning member 149
having a second annular fuel plenum 150. First annular flow
conditioning member 146 includes a first aerodynamic profile 154
that defines a first airfoil 155. Similarly, second annular flow
conditioning member 149 includes a second aerodynamic profile 157
that defines a second airfoil 158. In the exemplary aspect shown,
second annular flow conditioning member 149 is positioned
downstream from, and is axially off-set relative to first annular
flow conditioning member 146 within fluid flow passage 46. The
number and location of annular flow conditioning members 146 and
149 can vary. In a manner also similar to that described above, the
particular orientation of flow conditioning members 146 and 149
allows for enhanced fuel/air mixing while also leading to more
consistent flow velocities and reduced air/fuel separation within
fluid flow passage 46.
[0025] Reference will now be made to FIG. 8, wherein like reference
numbers represent corresponding parts in the respective views, in
describing a combustor assembly 200 in accordance with another
aspect of the exemplary embodiment. Combustor assembly 200 includes
a first annular flow conditioning member 206 having a first annular
fuel plenum 207 and a second annular flow conditioning member 209
having a second annular fuel plenum 210. First annular flow
conditioning member 206 includes a first aerodynamic profile 214
that defines a first airfoil 215. Similarly, second annular flow
conditioning member 209 includes a second aerodynamic profile 217
that defines a second airfoil 218. In the exemplary aspect shown,
first and second annular flow conditioning members 206 and 209 are
curved so as to form respective pressure and suction sides (not
separately labeled). In this manner, first and second flow
conditioning members 206 and 209 assist in turning fluid flow from
fluid flow passage 46 into the respective combustor (not separately
labeled) without developing flow separations in the fluid flow.
[0026] At this point it should be appreciated that the exemplary
embodiments describe an annular flow conditioning member(s) that is
suspended within a flow passage of a turbomachine combustor
assembly. The aerodynamic profile and the positioning of the
annular flow conditioning member enhances air/fuel mixing and also
leads to more consistent flow velocities particularly in axial and
tangential directions. Furthermore, by supporting annular flow
conditioning member 60 within fluid flow passage 46 separation of
fluid flow is reduced. It should also be understood that fuel may
be passed to the fuel plenum defined by the annular flow
conditioning member either through the support member instead of or
as a supplement to the fuel passage.
[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.
* * * * *