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특허 상세정보

Torsional damping for gas turbine engines

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/36    F01D-025/04    F01D-015/10    H02P-021/05    F02C-003/04    F02C-007/04    F02C-007/22    F16F-015/14    F16F-015/16    H02K-005/24    H02P-009/00    H02P-023/04    F16F-015/00    H02P-023/26   
출원번호 US-0018966 (2016-02-09)
등록번호 US-9938853 (2018-04-10)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    GE Aviation Patent Operation
인용정보 피인용 횟수 : 0  인용 특허 : 44
초록

The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so a...

대표
청구항

1. A method of damping torsional oscillations of a shaft system of a gas turbine engine assembly, comprising: providing pressurized air to a combustion chamber;injecting fuel into the pressurized air within the combustion chamber and igniting the fuel so as to raise a temperature and energy level of the pressurized air;providing combustion products from the combustion chamber to a turbine coupled via a shaft system to a generator; andgenerating, via the generator, AC voltage;converting, via a power converter, the AC voltage into DC voltage;converting, vi...

이 특허에 인용된 특허 (44)

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