Methods and apparatus for assembling gas turbine engines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/00
F02C-009/16
F23R-003/54
F23R-003/00
출원번호
UP-0358763
(2006-02-21)
등록번호
US-7631504
(2009-12-24)
발명자
/ 주소
Belsom, Keith Cletus
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
5인용 특허 :
13
초록▼
A combustor assembly is provided. The combustor assembly includes a combustion chamber and at least one transition portion extending downstream from the combustion chamber to facilitate channeling combustion gases from the combustor assembly. The assembly also includes at least one air control syste
A combustor assembly is provided. The combustor assembly includes a combustion chamber and at least one transition portion extending downstream from the combustion chamber to facilitate channeling combustion gases from the combustor assembly. The assembly also includes at least one air control system coupled to the at least one transition portion. The air control system including at least one biasing mechanism coupled to a controller to facilitate reducing emissions from the combustor assembly operation.
대표청구항▼
What is claimed is: 1. A method of assembling a gas turbine engine including at least one combustor, said method comprising: coupling at least one transition portion to the at least one combustor and to at least one gas turbine nozzle such that the at least one transition portion facilitates channe
What is claimed is: 1. A method of assembling a gas turbine engine including at least one combustor, said method comprising: coupling at least one transition portion to the at least one combustor and to at least one gas turbine nozzle such that the at least one transition portion facilitates channeling combustion gases discharged from the at least one combustor to the at least one gas turbine nozzle; defining a downstream combustion gas flow channel within the at least one transition portion; defining a substantially annular upstream airflow channel that is spaced substantially circumferentially about the downstream flow channel and located within a plenum; providing at least one air control system including at least one biasing mechanism and at least one piston coupled to a control mechanism; forming at least one seat within an opening defined in the at least one transition portion, wherein the opening extends between the downstream flow channel and the upstream flow channel, the seat configured to limit movement of the at least one piston; and coupling the air control system to the at least one transition portion to facilitate combustion during engine operation. 2. A method in accordance with claim 1 wherein coupling the air control system to at least one transition portion comprises coupling the air control system to at least one transition portion extending between the at least one combustor and a turbine assembly such that the biasing mechanism is biased against the piston within an enclosure that is coupled to a low pressure fluid source. 3. A method in accordance with claim 2 wherein coupling the air control system to at least one transition portion comprises: aligning the biasing mechanism and the piston substantially concentrically with respect to the opening defined in the at least one transition portion; and biasing the piston to selectively control a flow of air into the at least one combustor through the opening defined in the at least one transition portion. 4. A method in accordance with claim 3 wherein biasing the piston to selectively control a flow of air into the at least one combustor further comprises positioning the piston against the seat formed within the opening defined in the at least one transition portion. 5. A method of assembling a gas turbine engine in accordance with claim 3 wherein coupling the air control system to at least one transition portion further comprises coupling a plurality of air control systems circumferentially about the at least one transition portion. 6. A method of assembling a gas turbine engine in accordance with claim 3 wherein biasing the piston comprises positioning the biasing mechanism to bias the piston radially inward. 7. A method of assembling a gas turbine engine in accordance with claim 1 wherein coupling the air control system to at least one combustor further comprises coupling the control mechanism to the biasing mechanism to selectively control the flow of air into the at least one combustor based on gas turbine engine operating conditions. 8. A combustor assembly comprising: a combustion chamber; a gas turbine nozzle; at least one transition portion extending downstream from said combustion chamber to said gas turbine nozzle, said at least one transition portion facilitates channeling combustion gases from said combustion chamber to said gas turbine nozzle, wherein said transition portion defines a downstream combustion gas flow channel and a substantially annular upstream airflow channel that is spaced substantially circumferentially about said downstream flow channel and located within a plenum, and at least one seat formed within an opening defined in said at least one transition portion, wherein said opening extends between said downstream and upstream flow channels; and at least one air control system coupled to said at least one transition portion, said air control system comprising at least one biasing mechanism and at least one piston coupled to a controller, said at least one seat configured to limit the movement of said at least one piston. 9. A combustor assembly in accordance with claim 8 wherein said transition portion comprises a plurality of walls defining said transition portion, at least one of said plurality of walls comprises the opening extending therethrough, said opening facilitates a reduction of emissions from said combustor assembly. 10. A combustor assembly in accordance with claim 9 wherein said at least one air control system comprises at least one piston enclosure, said enclosure is coupled in flow communication with said transition portion and at least one low pressure fluid source, said enclosure houses at least a portion of said biasing mechanism and at least a portion of said at least one piston, said biasing mechanism is aligned substantially concentrically with respect to said opening defined in said transition portion. 11. A combustor assembly in accordance with claim 10 wherein said at least one air control system enclosure comprises an outer wall comprising a plurality of passages defined therein, wherein a first of said plurality of passages is coupled in flow communication with a high pressure fluid source, a second of said plurality of passages is coupled in flow communication with a combustion gas stream passage, and a third of said plurality of passages is coupled in flow communication with a low pressure fluid source. 12. A combustor assembly in accordance with claim 10 wherein said piston comprise a radially inner portion, a radially outer portion, and a center portion extending therebetween, said center portion having a diameter that is smaller than a diameter of said radially outer and radially inner portions. 13. A combustor assembly in accordance with claim 10 wherein said biasing mechanism biases said piston, said biasing mechanism positioned between an interior wall of said air control system enclosure and said piston. 14. A combustor assembly in accordance with claim 8 wherein said at least one control mechanism comprises at least one valve coupled between a low pressure fluid source and said at least one biasing mechanism for controlling a flow of air into said combustor during engine operation. 15. A gas turbine engine comprising: a compressor, at least one combustor assembly downstream from said compressor and comprising a combustion chamber, a gas turbine nozzle, and at least one transition portion extending downstream from said combustion chamber to said gas turbine nozzle to facilitate channeling combustion gases from said combustion chamber to said gas turbine nozzle, said transition portion defines a downstream combustion gas flow channel and a substantially annular upstream airflow channel that is spaced substantially circumferentially about said downstream flow channel and located within a plenum, and at least one seat formed within an opening defined in said at least one transition portion, said opening extends between said downstream and upstream flow channels; and at least one air control system coupled to said at least one transition portion, said air control system comprising at least one biasing mechanism and at least one piston coupled to a controller, said at least one seat configured to limit the movement of said at least one piston. 16. A gas turbine engine in accordance with claim 15 wherein said combustor assembly transition portion comprises at least one wall defining a flow boundary of said transition portion, said transition portion at least one wall comprises the at least one opening defined therein, said opening facilitates reducing emissions from said combustor assembly during engine operations. 17. A gas turbine engine in accordance with claim 16 wherein said combustor assembly at least one air control system comprises at least one enclosure, said enclosure is coupled in flow communication with at least one transition portion opening and with at least one low pressure fluid source, said enclosure houses at least a portion of said biasing mechanism and at least a portion of said piston, said biasing mechanism is aligned substantially concentrically with respect to at least one transition portion opening and with respect to said at least one piston. 18. A gas turbine engine in accordance with claim 17 wherein said combustor assembly at least one air control system enclosure comprises a plurality of openings, a first of said openings is coupled in flow communication with a high pressure fluid source, and a second of said openings is coupled in flow communication with a low pressure fluid source. 19. A gas turbine engine in accordance with claim 17 wherein said piston and said biasing mechanism are in contact, said biasing mechanism further contacts said air control system enclosure. 20. A gas turbine engine in accordance with claim 15 wherein said at least one control mechanism comprises: at least one valve coupled in flow communication to a low pressure fluid source to control a flow of air into said combustor during operation.
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이 특허에 인용된 특허 (13)
Meyer Franz-Josef (Marbach DEX), Combustion chamber for gas turbines.
Hessler, William K.; Popovic, Predrag; Nyberg, Charles, Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface.
Stoia, Lucas John; Romig, Bryan Wesley; Johnson, Thomas Edward; Stevenson, Christian Xavier, System and method for supplying a working fluid to a combustor.
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