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특허 상세정보

Method for setting a gear ratio of a fan drive gear system of a gas turbine engine

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-001/04    F01D-025/16    F02C-003/04    F02C-007/36    F02K-003/06    F02C-007/00    F01D-009/04   
출원번호 US-0337171 (2016-10-28)
등록번호 US-9816443 (2017-11-14)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 52
초록

A gas turbine engine includes an engine centerline longitudinal axis and a fan section including a fan with fan blades and rotatable about the engine centerline longitudinal axis. A low corrected fan tip speed less than about 1400 ft/sec and the low corrected fan tip speed is an actual fan tip speed determined at an ambient temperature divided by (Tram ° R)/(518.7 ° R)0.5, where T represents the ambient temperature in degrees Rankine. A bypass ratio greater than about 11 and a speed reduction device having a gear system with a gear ratio. A low and high ...

대표
청구항

1. A gas turbine engine comprising: an engine centerline longitudinal axis;a fan section including a fan with a plurality of fan blades and rotatable about the engine centerline longitudinal axis, wherein the fan has a low corrected fan tip speed less than 1400 ft/sec, wherein the low corrected fan tip speed is an actual fan tip speed at an ambient temperature divided by [(Tram ° R)/(518.7° R)]0.5, where Tram represents the ambient temperature in degrees Rankine;a bypass ratio greater than 13 and less than 20;a fan pressure ratio less than 1.48, wherein ...

이 특허에 인용된 특허 (52)

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