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특허 상세정보

Turbofan duct with noise suppression and boundary layer control

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/53B ; 244/1N ; 244/130 ; 244/209
출원번호 US-0813234 (1985-12-24)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 49  인용 특허 : 0
초록

A boundary layer control device is installed in the acoustically treated inlet duct of a turbofan engine. The device sucks off the turbulent boundary layer of air flowing over the inner or “air wetted”surface of the inlet during aircraft take-off, cruise and approach. The lip of the inlet can thus be made thinner to reduce drag during cruise without degradation of fan performance during take-off. The acoustic liner of the inlet comprises a microporous honeycomb sandwich structure through which air may be sucked at various locations through headers and co...

대표
청구항

An inlet duct for a high bypass ratio turbofan engine which produces thrust in the form of hot gases exhausted by a turbine and relatively cool air propelled by a fan driven by the turbine at a forward end thereof, the inlet duct including a generally cylindrical body having an inside diameter corresponding to a diameter of the fan, the body having a cellular noise suppressing structure forming a part of an inwardly facing surface of the body, the noise suppressing structure having a construction that absorbs fan noise over a wide range of frequencies an...

이 특허를 인용한 특허 피인용횟수: 49

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