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특허 상세정보

Gas turbine engine shaft bearing configuration

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-001/06    F02K-003/00    F02C-007/36    F01D-025/16    F02K-003/04    F02C-007/06   
출원번호 US-0219112 (2014-03-19)
등록번호 US-9194329 (2015-11-24)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 2  인용 특허 : 65
초록

A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

대표
청구항

1. A compressor module for a gas turbine engine comprising: a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path;a shaft providing a rotational axis;first and second bearings supporting the shaft relative to the intermediate case and the inlet case, respectively, wherein the first bearing is arranged in a first bearing support, the first bearing support removably secured to the intermediate case, and the second bearing is arranged in a second bearing support, the s...

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