ANNULAR FLOW CONDITIONING MEMBER FOR GAS TURBOMACHINE COMBUSTOR ASSEMBLY
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.
Latest General Electric Patents:
- Contrast imaging system and method
- Modular power distribution assembly and method of assembly thereof
- Methods for manufacturing blade components for wind turbine rotor blades
- Tissue specific time gain compensation methods and systems
- System and method having flame stabilizers for isothermal expansion in turbine stage of gas turbine engine
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.
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.
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.
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 INVENTIONAccording 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.
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.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
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:
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 INVENTIONWith reference to
As best shown in
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
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 (
Reference will now be made to
Reference will now be made to
Reference will now be made to
Reference will now be made to
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.
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.
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.
Type: Application
Filed: Oct 14, 2011
Publication Date: Apr 18, 2013
Applicant: GENERAL ELECTRIC COMPANY (Schenectady, NY)
Inventors: Madanmohan Manoharan (Chennai), Mahesh Bathina (Ongole)
Application Number: 13/273,372