|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/53B ; 244/1N ; 244/130 ; 244/209|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 49 인용 특허 : 0|
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...
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...