[특허]Vented tangential on-board injector for a gas turbine engine

Vented tangential on-board injector for a gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/12 F01D-001/02 F01D-005/08 F01D-011/00 F01D-011/02 F02C-007/18
출원번호	US-0609926 (2015-01-30)
등록번호	US-9945248 (2018-04-17)
발명자 / 주소	McCaffrey, Michael G
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Bachman & LaPointe, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 25

초록 ▼

An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

대표청구항 ▼

1. An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine, comprising: a first wall;a second wall spaced from said first wall to define an annular inlet about an engine axis; anda multiple of airfoil shapes between said first wall and said second wall to segregate discharge air from said annular inlet, and a multiple of bypass apertures each along an axis transverse to said engine axis, one of each of said multiple of apertures extends through one of said multiple of airfoil shapes and said respective first and second wall. 2. The on-board injector as recited in claim 1, wherein each of said multiple of airfoil shapes include a trailing edge arranged 80 degrees with respect to the engine axis. 3. The on-board injector as recited in claim 1, wherein each of said multiple of airfoil shapes include a trailing edge arranged 10 degrees with respect to a circumferential direction about the engine axis. 4. The on-board injector as recited in claim 1, wherein said multiple of airfoil shapes define a cascade exit to segregate the discharge air. 5. The on-board injector as recited in claim 1, wherein each of said multiple of airfoil shapes include a pressure side and a suction side, said pressure side in a rotational downstream position with respect to a coverplate about said engine axis. 6. The on-board injector as recited in claim 5, wherein said first wall includes a first wall portion with a multiple of apertures. 7. The on-board injector as recited in claim 6, further comprising an outer rim that extends from said first wall portion. 8. The on-board injector as recited in claim 7, further comprising a static seal that extends radially inward from said outer rim that extends from a radial portion of said first wall. 9. The on-board injector as recited in claim 8, further comprising a knife edge that extends from said coverplate to seal with said static seal. 10. The on-board injector as recited in claim 7, wherein said outer rim, a radial first wall portion and said first wall define a generally U-shape in cross-section. 11. The on-board injector as recited in claim 5, wherein said coverplate includes a multiple of coverplate apertures to receive the discharge air. 12. The on-board injector as recited in claim 1, wherein said second wall includes an extended portion with a multiple of apertures. 13. The on-board injector as recited in claim 1, wherein said multiple of bypass apertures are circular. 14. A system for a gas turbine engine comprising: a coverplate for a turbine rotor defined about an engine longitudinal axis, said coverplate including a multiple of coverplate apertures; andan on-board injector with a multiple of airfoil shapes between a first wall and a second wall to define an annular inlet about the engine longitudinal axis, said multiple of airfoil shapes operable to segregate and direct discharge air from the annular inlet toward said multiple of coverplate apertures, said on-board injector including a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis, one of each of said multiple of apertures extends through one of said multiple of airfoil shapes, said first wall, and said second wall. 15. The engine as recited in claim 14, wherein each of said multiple of airfoil shapes include a pressure side and a suction side, said pressure side in a rotational downstream position with respect to said coverplate about said engine axis. 16. The engine as recited in claim 13, wherein said multiple of airfoil shapes define a cascade exit to segregate the discharge air.

이 특허에 인용된 특허 (25)

Mize Christopher D. (Palm Beach Gardens FL) Pirsig William W. (Manchester CT) Vercellone Peter T. (North Haven CT), Anti-contamination thrust balancing system for gas turbine engines.
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Levine Richard (Bloomfield CT), Attachment for TOBI.
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Glasspoole David Frederick,CAX ; Schraenen Yvan,CAX, Cast on-board injection nozzle with adjustable flow area.
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Coulon, Sylvie; Stangalini, Gérard; Taillant, Jean-Claude; Adam, Gérard, Cooling the upstream end plate of a high pressure turbine by means of a system of dual injectors at the end of the combustion chamber.
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Charbonnel Jean-Louis (Le Mee sur Seine FRX) Naudet Jacky (Bondoufle FRX) Stangalini Grard J. (Fontainebleau FRX), Device for checking the clearances of a gas turbine compressor casing.
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Smoke, Jason; Mitlin, Bob; MirzaMoghadam, Alexander, Direct transfer axial tangential onboard injector system (TOBI) with self-supporting seal plate.
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Robert Paul Czachor ; William Carl Ruehr, Fan casing liner support.
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Urban Jrg (Ludwigshafen DEX), Fluid flow machine with variable clearances between the casing and a fluid flow guiding insert in the casing.
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Yuri, Masanori; Laurello, Vincent; Hada, Satoshi, Gas turbine.
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Yuri, Masanori; Laurello, Vincent; Ellis, Charles; Noguchi, Mitsuhiro; Fujii, Keita, Gas turbine and method of bleeding gas therefrom.
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Schwarz, Frederick M.; Smith, J. Walter, Gas turbine engine blade tip clearance apparatus and method.
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Czachor Robert P. (Cincinnati OH), Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases throug.
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Arilla,Jean Baptiste; Galland,Alain; Hacault,Michel Gerard Paul; Maffre,Jean Philippe, Gas turbine stator.
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Chambon Frederic,FRX ; Michel Lestoille Patrick Didier,FRX ; Mouchel Jacques Henri,FRX ; Taillant Jean-Claude,FRX, Labyrinth disk with built-in stiffener for turbomachine rotor.
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Taylor,Steven Mitchell; Spencer,Christina Marie; Licu,Dragos Nicolae, Methods and apparatus for controlling gas turbine engine rotor tip clearances.
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Wilson, Jr.,Jack W., Passive clearance control.
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Carpenter Kevin D. (Tequesta FL) Wiedemer John D. (Wellington FL) Smith ; Jr. Paul A. (Palm Beach Gardens FL), Rotor blade outer tip seal apparatus.
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Thomas ; Jr. Theodore T. (Loveland OH) Rieck ; Jr. Harold P. (West Chester OH), Stator to rotor flow inducer.
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Floyd, II, Donald E.; Ballard, Jr., Henry G.; Miller, Brad, System and method for clearance control in a rotary machine.
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Maier Mark S. (North Palm Beach FL) Eng Jesse (Jupiter FL), TOBI.
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Largillier Christian,FRX ; Marchi Marc Roger,FRX ; Palmisano Laurent,FRX ; Stangalini Gerard Jacques,FRX, Turbine disk cooling device.
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Liu Xiaoliu,CAX, Turbine engine having improved high pressure turbine cooling.
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Brown Wesley D. (Jupiter FL) Hill Edward C. (Tequesta FL) Vercellone Peter T. (Lake Worth FL), Turbine rotor retention system.
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Behaghel, Laurent; Mourlan, Jean-Pierre Andre Joseph; Stangalini, Gerard Jacques, Turbomachine comprising a system for cooling the downstream face of an impeller of a centrifugal compressor.
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Soechting, Friedrich O.; Bessette, Alan D., Vane platform trailing edge cooling.
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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

Vented tangential on-board injector for a gas turbine engine 원문보기

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Vented tangential on-board injector for a gas turbine engine 원문보기

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연구과제 타임라인

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