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특허 상세정보

Variable contour nacelle assembly for a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/042    F02K-003/06    B64D-033/02    F02C-007/045   
출원번호 US-0772287 (2007-07-02)
등록번호 US-9228534 (2016-01-05)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds
인용정보 피인용 횟수 : 0  인용 특허 : 61
초록

A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition ...

대표
청구항

1. A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section;a nacelle assembly at least partially surrounding at least one of said compressor section, said combustor section and said turbine section, wherein said nacelle assembly includes an inlet lip section and a cowl section that each include an adjustable contour, each of said inlet lip section and said cowl section including a first surface that faces radially inward and a second surface that faces radially outward, each of said first surfaces and said secon...

이 특허에 인용된 특허 (61)

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