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특허 상세정보

Turbojet nacelle and method for controlling separation in a turbojet nacelle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02    B64C-021/04   
미국특허분류(USC) 244/053B; 244/207; 244/204
출원번호 US-0326604 (2008-12-02)
등록번호 US-8640986 (2014-02-04)
우선권정보 FR-07 59488 (2007-12-03)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Patterson Thuente Pedersen, P.A.
인용정보 피인용 횟수 : 2  인용 특허 : 20
초록

An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (Ft) into the internal volume (V) of the nacelle, said blowing means being provided in a wall of the air intake of the nacelle in the supersonic area of said air intake. The invention also concerns a method for controlling separation in an aircraft nacelle, wherein a tangential airflow is injected (Ft) into the internal volume (V) of the nacelle in the locally supersonic area of the air intake so as to pull the main airflow (F) into the extension of the inner wa...

대표
청구항

1. Aircraft turbojet nacelle wherein it comprises blowing means intended to inject a tangential airflow (F1) taken from outside the nacelle into an internal volume (V) of the nacelle, said blowing means being provided in a wall of an air intake of the nacelle in a supersonic area of said air intake, the blowing means comprising at least one air inlet line equipped with a rear end and a front end, the rear end ending at an outer wall of the nacelle and capable of taking the tangential airflow from outside the nacelle and the front end ending in the nacell...

이 특허에 인용된 특허 (20)

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  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
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