[특허]Valve system for a gas turbine engine

Valve system for a gas turbine engine 원문보기

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국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/00 B63H-025/46
출원번호	US-0053591 (2008-03-22)
등록번호	US-8402744 (2013-03-26)
발명자 / 주소	Schirtzinger, Gary A.
출원인 / 주소	Pratt & Whitney Rocketdyne, Inc.
대리인 / 주소	Carlson, Gaskey & Olds
인용정보	피인용 횟수 : 0 인용 특허 : 36

초록

A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher pressure plenum into a lower pressure flowpath.

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1. A valve system intermediate a secondary flow path and a primary flow path of a gas turbine engine comprising: a valve seat defining a flow passage there through between a secondary flow path and a primary flow path; anda plurality of poppet valves movable relative said valve seat between an open position and a closed position with regard to said flow passage, said flow passage including a structure that directs flow through said flow passage;wherein said plurality of poppet valves, and said valve seat define a corresponding plurality of flow passages between the secondary flow path and the primary flow path; andan actuator system that is operable to selectively move said plurality of poppet valves; anda controller in communication with said actuator system and operable to command said actuator system to move said plurality of poppet valves wherein said controller is operable to command said actuator system to move said plurality of poppet valves sequentially. 2. The system as recited in claim 1, wherein said plurality of poppet valves are movable along a valve axis relative to said valve seat to define an open position and a closed position. 3. The system as recited in claim 1, wherein said valve seat is mounted to an inner cooling liner structure of a gas turbine engine. 4. The system as recited in claim 1, wherein said valve seat is formed into an inner cooling liner structure of a gas turbine engine. 5. The system as recited in claim 1, further comprising an actuator system which independently operates each of said plurality of poppet valves. 6. The system as recited in claim 1, wherein said structure is selected from the group consisting of a mesh, a grid, a metering hole and a honeycomb. 7. The system as recited in claim 1, wherein said structure includes a mesh. 8. The system as recited in claim 1, wherein said structure includes a grid. 9. The system as recited in claim 1, wherein said structure includes a honeycomb. 10. The system as recited in claim 1, wherein said structure includes a metering hole. 11. A gas turbine engine comprising: an engine duct structure and an inner cooling liner structure which at least partially define a secondary flow path and a primary flow path along a longitudinal axis;a valve seat mounted to said inner cooling liner structure; anda plurality of poppet valves movable relative said valve seat between an open position away from the longitudinal axis and a closed position toward the engine axis;said plurality of poppet valves, and said valve seat define a corresponding plurality of flow passages between the secondary flow path and the primary flow path; andan actuator system that is operable to selectively move said plurality of poppet valves; anda controller in communication with said actuator system and operable to command said actuator system to move said plurality of poppet valves wherein said controller is operable to command said actuator system to move said plurality of poppet valves sequentially. 12. The engine as recited in claim 11, wherein said valve seat is flush with said inner cooling liner structure. 13. The system as recited in claim 11, wherein said actuator system operates said plurality of poppet valves and said actuator system including a linkage which extends through said engine duct structure. 14. The engine as recited in claim 11, wherein said secondary flow path is defined radially about said primary flow path. 15. The system as recited in claim 11, wherein said controller is operable to command said actuator system to move said plurality of poppet valves individually. 16. The system as recited in claim 11, wherein said plurality of flow passages include a plurality of corresponding structures that direct flow through the plurality of flow passages. 17. A method of a controlling communication of a secondary flow path with a primary flow path of a gas turbine engine comprising the steps of: selectively moving plurality of poppet valves relative a valve seat mounted intermediate the secondary flow path and the primary flow path between an open position and a closed position;wherein said plurality of poppet valves, and said valve seat define a corresponding plurality of flow passages between the secondary flow path and the primary flow path;providing an actuator system that is operable to selectively move said plurality of poppet valves; andproviding a controller in communication with said actuator system and operable to command said actuator system to move said plurality of poppet valves wherein said controller is operable to command said actuator system to move said plurality of poppet valves sequentially. 18. A method as recited in claim 17, further comprising: opening said plurality of poppet valves outwardly relative the primary flow path. 19. A method as recited in claim 17, further comprising: opening said plurality of poppet valves individually. 20. A method as recited in claim 17, further comprising: sourcing the primary airflow to the primary flow path from a primary combustion core gas exhaust flow of the gas turbine engine. 21. A method as recited in claim 20, further comprising: sourcing the secondary airflow to the secondary flow path from a source different than the primary combustion core gas exhaust flow of the gas turbine engine. 22. A method as recited in claim 21, further comprising: sourcing the secondary airflow to the secondary flow path from an advent cycle third stream fan flow which from a fan section of the gas turbine engine.

이 특허에 인용된 특허 (36)

Lee, Douglas; Anderson, J. Thomas; Hershberger, Brian K., Apparatus and method for controlling primary fluid flow using secondary fluid flow injection.
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Ream Jeffrey L. (Tolland CT) Bubello Robert (North Meriden CT), Buffer region for the nacelle of a gas turbine engine.
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Ream Jeffrey L. (Tolland CT) Bubello Robert (North Meriden CT), Buffer region for the nacelle of a gas turbine engine.
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Edelman, Raymond B.; Morrison, Jr., Calvin Q.; Pederson, Robert J.; Morris, Donald H.; Schmotolocha, Stephen N., Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance.
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Schmotolocha, Stephen N.; Morris, Donald H.; Pederson, Robert J.; Edelman, Raymond B.; Morrison, Jr., Calvin Q., Compact swirl augmented afterburners for gas turbine engines.
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Bouiller Jean G. (Brunoy FRX) Jourdain Grard E. A. (Saintry sur Seine FRX), Compressor blow-off arrangement.
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Murphy,Michael J.; Cowan,Curtis C.; Paul,Stephen A.; Allore,James P.; Harris,Meggan, Convergent/divergent nozzle with modulated cooling.
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Nash Dudley O. (Cincinnati OH) Herzner Frederick C. (Fairfield OH), Coolant pressure regulating apparatus.
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Marini,Remo; Sreekanth,Sri, Coverplate deflectors for redirecting a fluid flow.
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Girgis,Sami; Marini,Remo, Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine.
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Brockett Walter D. (North Haven CT), Ejector assisted compressor bleed.
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Liang George P. ; Yeager William J. ; Soileau John F., Ejector extension cooling for exhaust nozzle.
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Burke Thomas A. (Mentor OH) Scheuerman Curtis H. (Newbury OH), Flow dividing valve.
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Corr ; II Robert A. (Scotia NY), Gas turbine combustor having poppet valves for air distribution control.
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Macfarlane,Ian; Szlanta,Zenon; Mitrovic,Lazar; Morgan,Keith, Gas turbine engine architecture.
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Cesar Aguilera Montoya, Gas turbine engine with increased fuel efficiency and method for accomplishing the same.
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Ioan Sasu CA; Andre LeBlanc CA; Michel Bellerose CA, Integrated duct diffuser.
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Frost Wilson (Fairfield OH) Wood Peter J. (Cincinnati OH) Bobo Melvin (Cincinnati OH) Little Daniel R. (West Chester OH), Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine.
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Marvin Ira E. (Russell Springs KY), Method of pressure-ratio control of gas turbine engine.
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Prociw,Lev Alexander; Shafique,Harris; Sokalski,John; Pelletier,Claude Raymond, Nested channel ducts for nozzle construction and the like.
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Aitchison,Paul Archibald; Germain,Patrick David; Smith,Henry, Normally open reverse flow flapper valve.
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Wernberg, Donald E.; Tysver, John D., Nozzle assembly with flow divider and ecology valve.
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Jourdain Grard E. A. (Saintry sur Seine FRX) Soligny Marcel R. (Chevilly-Larue FRX), Ring structure and compressor blow-off arrangement comprising said ring.
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Renggli,Bernard James, Split shroud exhaust nozzle.
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Koshoffer,John Michael, Trapped vortex cavity afterburner.
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Bartos James W., Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and a.
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Ward, Eric J., Valve assembly for gas turbine engine.
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Even-Nur Michael (Cincinnati OH) Hoffmann ; Jr. Carl J. (West Chester OH) Kraimer Robert H. (West Chester OH), Variable area bypass valve assembly.
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Sanders,Noel A; Bourne,Carl C; Moran,Anthony J; Fletcher,Paul; Walsh,Philip P, Variable geometry combustor.
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Anderson, Morris G.; Banta, Paul W.; Brackin, James W.; Romano, Robert; Zmora, David W., Variable geometry ejector for a bleed air system using integral ejector exit pressure feedback.
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Valve system for a gas turbine engine 원문보기

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