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특허 상세정보

Bypass air scoop for gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-011/24   
미국특허분류(USC) 415/115; 415/117; 415/173.2; 415/176; 415/178
출원번호 US-0335660 (2008-12-16)
등록번호 US-8092153 (2012-01-10)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Norton Rose or LLP
인용정보 피인용 횟수 : 4  인용 특허 : 41

A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.


1. A gas turbine engine comprising a fan assembly, a compressor assembly, a combustion gas generator assembly, a turbine assembly and an annular bypass air duct for directing a bypass air flow driven by the fan assembly to pass therethrough, the annular bypass air duct being defined between inner and outer duct walls, a plurality of struts radially extending between the inner and outer duct walls, at least one of the struts having an aerodynamic fairing located the bypass air duct, the at least one strut including an air scoop in the fairing, the air sco...

이 특허에 인용된 특허 (41)

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