[특허]Turbofan gas turbine engine

Turbofan gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/04
출원번호	US-0123544 (1987-11-20)
우선권정보	GB-0030754 (1986-12-23)
발명자 / 주소	Coplin John F. (Derby GB2)
출원인 / 주소	Rolls-Royce plc (London GB2 03)
인용정보	피인용 횟수 : 110 인용 특허 : 0

초록 ▼

A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor and a core engine is provided with a diffuser. The diffuser is positioned axially between the booster compressor and the compressor of the core engine to efficiently diffuse the air from the fan to the compressor of the core engine. The diffuser comprises a plurality of circumferentially arranged geodesic pipe diffusers, the pipe diffusers extend axially and radially and the outlets of the pipe diffusers are displaced circumferentially by an angle of between 20°and 60°with respect to the inlets of the pipe diffusers. The geodesic pipe diffusers allows the airflow between the fan and the core engine to be diffused adequately without compromising the efficiency of the core engine, or the high mass flow rate of the fan and also minimizes the length, weight and drag of the gas turbine engine.

대표청구항 ▼

A turbofan gas turbine engine comprising in axial flow series a fan, a booster compressor means, a compressor means, a combustor means, a first turbine means and a second turbine means, the first turbine means being arranged to drive the compressor means, the second turbine means being arranged to drive the fan and the booster compressor means, a diffuser means being positioned axially between the booster compressor means and the compressor means, the diffuser means comprising a plurality of circumferentially arranged geodesic pipe diffusers, each geodesic pipe diffuser having an inlet at the upstream end and an outlet at the downstream end, the outlet of each geodesic pipe diffuser being displaced circumferentially by an angle with respect to the inlet thereof, each geodesic pipe diffuser following substantially the shortest path between the inlet and the outlet thereof; said geodesic diffusers extending both axially and radially inwardly and each following substantially a straight line path between said respective inlet and outlet thereof.

이 특허를 인용한 특허 (110)

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Lord, Wesley K.; Malecki, Robert E.; Qiu, Yuan J.; Rose, Becky E.; Gilson, Jonathan, Low pressure ratio fan engine having a dimensional relationship between inlet and fan size.
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Morris Green Penn ; Bala Corattiyil, Method and apparatus for centering rotor assembly damper bearings.
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Sheridan, William G.; Hasel, Karl L., Method for setting a gear ratio of a fan drive gear system of a gas turbine engine.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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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

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연합인증

Turbofan gas turbine engine 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

이 특허를 인용한 특허 (110)

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연합인증

Turbofan gas turbine engine 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

전체(0) 논문(0) 특허(0) 보고서(0)

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이 특허를 인용한 특허 (110)

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