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특허 상세정보

High bypass ratio counterrotating turbofan engine

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/072   
미국특허분류(USC) 60/2261 ; 60/268 ; 60/39162 ; 415/65
출원번호 US-0166749 (1988-03-10)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 143  인용 특허 : 4
초록

A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the ...

대표
청구항

A gas turbine engine comprising: a unitary gas generator effective for generating combustion gases; a counterrotatable power turbine completely aft of said gas generator including first and second interdigitated counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively; a counterrotatable fan section completely forward of said gas generator including a first fan blade row connected to said first drive shaft and a second fan blade row connected to said second drive shaft; and a counterrotatable booster compress...

이 특허를 인용한 특허 피인용횟수: 143

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