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특허 상세정보

Supersonic engine inlet diffuser with deployable vortex generators

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/042    F02C-007/04   
출원번호 US-0454306 (2012-04-24)
등록번호 US-9429071 (2016-08-30)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    David M. Quinlan, P.C.
인용정보 피인용 횟수 : 1  인용 특허 : 26

A flow control device generates counter-rotating vortices in the boundary layer of the flow in a supersonic inlet diffuser for an aircraft turbine engine. The flow control device comprises a flap attached to the duct wall for selective deployment, wherein it extends into the boundary layer, and retraction, wherein it lies substantially flush with the duct wall. In one embodiment an actuating mechanism comprising one or more shape-memory alloy wires moves the flap between two stable positions. In another embodiment the deployment height of the flap can be...


1. An inlet diffuser for introducing air flow to a turbine engine, the diffuser comprising: an inlet duct having a portion bounded by mutually facing duct walls for accepting air traveling at a velocity in excess of the speed of sound in the air (M >1) and passing air flow traveling in said duct at M >1 through a shock front between said facing duct walls at a location in said inlet duct upstream of the turbine engine to decelerate the air flow to a velocity less than the speed of sound in the air (M <1), wherein a boundary layer proximate to at least on...

이 특허에 인용된 특허 (26)

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