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Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor 원문보기

IPC분류정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판)
  • F02K-003/04
출원번호 US-0087428 (2002-03-01)
발명자 / 주소
  • Seda, Jorge F.
  • Dunbar, Lawrence W.
  • Szucs, Peter N.
  • Brauer, John C.
  • Johnson, James E.
출원인 / 주소
  • General Electric Company
대리인 / 주소
    Herkamp, Nathan D.
인용정보 피인용 횟수 : 128  인용 특허 : 20

초록

An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan b

대표청구항

An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan b

이 특허에 인용된 특허 (20)

  1. Freid Wilbert B. (Bridgton ME), Aircraft gas turbine engine thrust mount.
  2. Moniz Thomas ; Hauser Ambrose A. ; Seda Jorge F., Bearing lubrication configuration in a turbine engine.
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  20. Giffin ; III Rollin G. (Cincinnati OH), Variable specific thrust turbofan engine.

이 특허를 인용한 특허 (128)

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