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특허 상세정보

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

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/04   
미국특허분류(USC) 060/226.1; 060/268
출원번호 US-0087428 (2002-03-01)
발명자 / 주소
출원인 / 주소
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 blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressu...

대표
청구항

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 blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressu...

이 특허에 인용된 특허 (20)

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