System and method for flow control in gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0115018
(2011-05-24)
등록번호
US-8826667
(2014-09-09)
발명자
/ 주소
Melton, Patrick Benedict
Crawley, Bradley Donald
Cihlar, David William
Rohrssen, Robert Joseph
Chila, Ronald James
출원인 / 주소
General Electric Company
대리인 / 주소
Fletcher Yoder P.C.
인용정보
피인용 횟수 :
1인용 특허 :
27
초록▼
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sle
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
대표청구항▼
1. A system, comprising: a gas turbine combustor, comprising:a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner;an air passage between the combustion liner and the flow sleeve;a structure extending completely between the combustion liner and the f
1. A system, comprising: a gas turbine combustor, comprising:a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner;an air passage between the combustion liner and the flow sleeve;a structure extending completely between the combustion liner and the flow sleeve in the air passage, wherein the structure obstructs an airflow path through the air passage; andan aerodynamic wake reducer in the air passage, wherein the aerodynamic wake reducer is configured to redirect an airflow around the structure to reduce a wake region associated with and downstream of the structure, the aerodynamic wake reducer comprises a leading edge and a trailing edge, the leading edge faces toward the airflow path, the trailing edges faces away from the airflow path, and a trailing edge angle of the aerodynamic wake reducer is less than a leading edge angle of the aerodynamic wake reducer. 2. The system of claim 1, wherein the aerodynamic wake reducer comprises a flow control surface extending at least partially around the structure, and the flow control surface has an aerodynamic shape. 3. The system of claim 2, wherein the flow control surface comprises first and second surfaces disposed on opposite first and second sides of the structure, the first surface extends between the leading edge and the trailing edge on the first side of the structure, and the second surface extends between the leading edge and the trailing edge on the second side of the structure. 4. The system of claim 3, wherein the first and second surfaces converge toward one another along the airflow path toward the trailing edge. 5. The system of claim 1, wherein the aerodynamic wake reducer comprises a flow control surface that curves around the structure from the leading edge to the trailing edge of the structure. 6. The system of claim 5, wherein the structure comprises an elongated structure having a curved cross-section, and the flow control surface comprises an airfoil shaped cross-section disposed about the curved cross-section. 7. The system of claim 5, wherein the structure comprises an elongated structure having a rectangular cross-section, and the flow control surface comprises an airfoil shaped cross-section disposed about the rectangular cross-section. 8. The system of claim 5, wherein the aerodynamic wake reducer comprises an airfoil shaped wall having the flow control surface, the airfoil shaped wall is disposed at an offset distance from an exterior surface of the structure, and at least one support extends between the structure and the airfoil shaped wall. 9. The system of claim 1, comprising a fuel injector disposed downstream of the combustion liner and the flow sleeve in an annulus formed by a cap, wherein the fuel injector obstructs the airflow path through the air passage downstream from the structure, and the aerodynamic wake reducer is configured to reduce a wake in the airflow from the structure. 10. The system of claim 1, wherein the structure comprises a cross-fire tube, a flame detector, a spark plug, a boss, a spacer, a pressure probe, an axially staged air injector, a sensor, or a combination thereof. 11. The system of claim 1, wherein the structure and the aerodynamic wake reducer are a one-piece structure. 12. The system of claim 1, wherein the structure comprises a first alignment feature, the aerodynamic wake reducer comprises a second alignment feature, and the first and second alignment features mate with one another to align the aerodynamic wake reducer with the airflow path. 13. A system, comprising: an aerodynamic turbine wake reducer configured to reduce a wake in a wake region downstream from a structure obstructing a gas flow in a gas flow passage of a gas turbine engine, wherein the structure extends completely between a combustion liner and a flow sleeve in the gas flow passage, wherein the aerodynamic turbine wake reducer comprises a flow control surface configured to at least partially surround the structure, the aerodynamic turbine wake reducer is configured to mount upstream of a fuel injector disposed in the gas flow passage, the aerodynamic wake reducer comprises a leading edge and a trailing edge, the leading edge faces toward the gas flow, the trailing edges faces away from the gas flow, and a trailing edge angle of the aerodynamic wake reducer is less than a leading edge angle of the aerodynamic wake reducer. 14. The system of claim 13, wherein the flow control surface comprises an airfoil shaped cross-section. 15. The system of claim 13, wherein the structure and the flow control surface collectively define an airfoil shaped cross-section. 16. The system of claim 13, wherein the aerodynamic turbine wake reducer comprises a first component and a second component, and wherein the first and second components couple with one another around the structure. 17. A method, comprising: reducing a wake in a wake region downstream from a structure that obstructs an airflow along an airflow passage between a combustion liner and a flow sleeve of a gas turbine combustor using an aerodynamic wake reducer coupled to the structure, wherein the structure extends completely between the combustion liner and the flow sleeve in the airflow passage, and wherein reducing the wake comprises:flowing the airflow toward a leading edge of the aerodynamic wake reducer;dividing the airflow into a first flow and a second flow around the structure in the airflow passage;aerodynamically combining the first and second flows into the wake region in the airflow passage downstream of the structure; andflowing the airflow away from a trailing edge of the aerodynamic wake reducer, wherein a trailing edge angle of the aerodynamic wake reducer is less than a leading edge angle of the aerodynamic wake reducer. 18. The method of claim 17, comprising flowing the first and second flows about opposite paths along an aerodynamic flow control surface, wherein the aerodynamic flow control surface at least partially surrounds the structure. 19. The method of claim 18, comprising injecting a fuel from a fuel injector downstream of the aerodynamic flow control surface, wherein the fuel injector is disposed downstream of the combustion liner and the flow sleeve in an annulus formed by a cap. 20. The system of claim 1, wherein the gas turbine combustor comprises a first flow direction of combustion gases in the combustion region and a second flow direction of air along the airflow path, wherein the first and second directions are opposite from one another. 21. A system, comprising: a gas turbine combustor, comprising: a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner;an air passage between the combustion liner and the flow sleeve;a structure extending between the combustion liner and the flow sleeve in the air passage, wherein the structure obstructs an airflow path through the air passage;an aerodynamic wake reducer in the air passage, wherein the aerodynamic wake reducer is configured to redirect an airflow around the structure to reduce a wake region associated with and downstream of the structure; anda fuel injector disposed downstream of the combustion liner and the flow sleeve in an annulus formed by a cap, wherein the fuel injector obstructs the airflow path through the air passage downstream from the structure, and the aerodynamic wake reducer is configured to reduce a wake in the airflow from the structure. 22. A method, comprising: reducing a wake in a wake region downstream from a structure that obstructs an airflow along an airflow passage between a combustion liner and a flow sleeve of a gas turbine combustor using an aerodynamic wake reducer coupled to the structure, wherein reducing the wake comprises:dividing the airflow into a first flow and a second flow around the structure in the airflow passage;aerodynamically combining the first and second flows into the wake region in the airflow passage downstream of the structure;comprising flowing the first and second flows about opposite paths along an aerodynamic flow control surface, wherein the aerodynamic flow control surface at least partially surrounds the structure; andinjecting a fuel from a fuel injector downstream of the aerodynamic flow control surface, wherein the fuel injector is disposed downstream of the combustion liner and the flow sleeve in an annulus formed by a cap.
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