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특허 상세정보

Gas turbine engine with fan variable area nozzle for low fan pressure ratio

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/00    F02C-009/20    B64D-033/04    F02K-001/30    F02K-001/72    F01D-005/02    F01D-015/12    F01D-017/14    F01D-025/24    F02C-003/04    F02C-009/18   
출원번호 US-0340810 (2011-12-30)
등록번호 US-9494084 (2016-11-15)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 2  인용 특허 : 39
초록

A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

대표
청구항

1. A gas turbine engine comprising: a core nacelle defined about an engine centerline axis;a core engine at least partially disposed within the core nacelle;a fan section with twenty (20) or less fan blades;a gear system driven by the core engine to drive said fan section;a fan nacelle mounted at least partially around said fan section and said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan section having a fan pressure ratio less than 1.45;a variable fan nozzle axially movable relative to the fan nacelle, the variable f...

이 특허에 인용된 특허 (39)

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