[특허]Gas turbine engine clearance control

Gas turbine engine clearance control 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/08
출원번호	US-0078218 (1993-06-22)
국제출원번호	PCT/GB91/01964 (1991-11-08)
§371/§102 date	19930622 (19930622)
국제공개번호	WO-9211444 (1992-07-09)
발명자 / 주소	Mills Stephen J. (Derbyshire GB2) Monico Robin D. (Derby GB2) Bradley Andrew J. (Derbyshire GB2)
출원인 / 주소	Rolls-Royce plc (London GB2 03)
인용정보	피인용 횟수 : 28 인용 특허 : 0

초록 ▼

A gas turbine engine includes a casing cooling system which operates in one of two conditions, the first being operational at engine cruise, where all of the cooling air is initially directed onto a specific region of the casing; under full power conditions, some of the cooling air is directed onto the specific casing region and the reminder directed onto the reminder of the casing; the cooling system operates to optimize turbine blade/casing radial clearances.

대표청구항 ▼

A gas turbine engine turbine comprising a casing enclosing a plurality of annular arrays of rotor aerofoil blades, said blades being arranged in radially spaced apart relationship with said casing, means being provided to direct cooling air onto the outer surface of said casing to provide cooling thereof, control means being provided to control the distribution of cooling air so directed onto said casing between two circumferential axially adjacent regions of said casing, one of said region being axially forward and the other rearward of said forward region, means being provided to facilitate a flow of cooling air from the forward of said regions to the rearward of said regions, said control means being adapted to vary the distribution of said cooling air between a first condition in which all of said cooling air is initially directed onto the forward region of said casing and a second condition in which some of said cooling air is initially directed onto the forward regions of said casing and the remainder is directed only onto the rearward region of said casing, a manifold being located externally of the forward region of said casing, said manifold being adapted to be supplied with cooling air and to direct that cooling air onto said forward region of said casing to provide at least impingement cooling thereof, said casing having walls positioned so that at least some of the cooling air directed onto said forward region of said casing to cause impingement cooling thereof is subsequently caused to flow over the rearward region of said casing to provide convection cooling thereof, pipe members being provided to divide the cooling air directed onto said forward region of said casing into two portions with one portion subsequently caused to flow over said forward region in a generally upstream direction and the other portion in a generally downstream direction to provide convection cooling thereof.

이 특허를 인용한 특허 (28)

Legare, Pierre-Yves; Mah, Stephen, Active tip clearance control arrangement for gas turbine engine.
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Van Der Woude, Matthijs, Air guiding device and turbo engine with air guiding device.
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Boeck, Alexander, Arrangement for the cooling of the casing of an aircraft gas turbine engine.
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Feldmann, Manfred; Sangl, Janine; Kaltenbach, Sebastian; Lorenz, Joachim, Axial seal in a casing structure for a fluid flow machine.
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Spring Samuel D. ; Carita Robert J. ; Stocking Herbert A., Bay cooled turbine casing.
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Chehab,Abdullatif; Little,David A., Blade tip clearance control.
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Strecker, Steven; Hui, Hong-Wei, Bypass air scoop for gas turbine engine.
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Snook, Daniel David, Clearance control system for a gas turbine.
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Thies, Robert, Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air.
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Wang, Cheng-Zhang; Glahn, Jorn A.; Cloud, David F.; Munsell, Peter M.; Crawley, Jr., Clifton J.; Newman, Robert; Stearns, Michelle Diana, Engine mid-turbine frame transfer tube for low pressure turbine case cooling.
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Todorovic, Predrag, Fully integrated air guide element.
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Tillman, Don; Gage, Raymond; Barrett, Rich, Gas turbine engine turbine blade tip active clearance control system and method.
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Chehab, Abdullatif M.; Little, David A., Gas turbine engine with structure for directing compressed air on a blade ring.
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Zawilinski, David; Dean, W. Clark, Helical spring damper.
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Ireland, Peter T; Newcombe, Gareth; Mullender, Andrew J, Impingement cooling arrangement for a gas turbine engine.
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Urbassik, Ryan Michael; Estridge, Scott Anthony; Ruiz, Rafael; Proctor, Robert; Albers, Robert J.; Hansell, Kevin Stephen, Method and apparatus for operating gas turbine engines.
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Reed, Robert Joseph, Method and apparatus to control part-load performance of a turbine.
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Laurello, Vincent P., Radial active clearance control for a gas turbine engine.
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Bacic, Marko; Lewis, Leo Vivian; Irving, Robert John, Rotor blade tip clearance control.
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Chehab, Abdullatif M., Turbine blade tip clearance control.
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Joe, Christopher R.; Ward, Daniel A., Turbine blade tip clearance control.
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Joe, Christopher R.; Ward, Daniel A., Turbine blade tip clearance control.
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Morrill, Daniel Lawrence, Turbine case cooling system.
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Bintz, Matthew E.; Malmborg, Eric W.; Gendrich, Charles P., Turbine engine rotating cavity anti-vortex cascade.
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Bintz, Matthew E.; Schutte, Peter T.; Bifulco, Anthony R.; Malmborg, Eric W., Turbine engine rotating cavity anti-vortex cascade.
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Bintz, Matthew E.; Schutte, Peter T.; Bifulco, Anthony R.; Malmborg, Eric W., Turbine engine rotating cavity anti-vortex cascade.
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Pierre Sylvain ; Dobson Martin John,CAX, Turbine passive thermal valve for improved tip clearance control.
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Franconi, Robert B.; Goodman, Robert B.; MacDonald, Scott R.; Mazzone, Paul, Turbofan jet engine having a turbine case cooling valve.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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연합인증

Gas turbine engine clearance control 원문보기

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Gas turbine engine clearance control 원문보기

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