|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||137/151 ; 244/53B|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 26 인용 특허 : 0|
There is disclosed an air inlet for a turbine engine suitable for use on a short takeoff and landing (STOL), a vertical takeoff and landing (VTOL) or a conventional takeoff and landing (CTOL) type of aircraft. A critical region in which critical flow occurs under certain conditions communicates with a less critical region of lower static pressure. Air is drawn away from the critical region and reinjected into the air flow at the less critical region. In one embodiment a circumferentially extended slot is provided in the inner surface of the air inlet at ...
An air inlet for an aircraft turbine engine, said inlet being an annular body having inner and outer annular surfaces with an annular lip at its foreward end and a throat downstream of said lip, the minimum diameter of said throat lying on a plane perpendicular to the axis of said inlet diffuser, the improvement comprising: a circumferential plenum chamber formed in said diffuser around said throat; a primary aperture formed in said inner annular surface downstream of the plane of said throat at the windward side of said inlet in communication with said ...