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특허 상세정보

System for cooling blades in a gas turbine

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02G-003/00    F02C-005/00   
미국특허분류(USC) 60/039.182 ; 60/039.75 ; 415/115 ; 415/117
출원번호 US-0960466 (1997-10-29)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Alston & Bird LLP
인용정보 피인용 횟수 : 70  인용 특허 : 8
초록

Also, A gas turbine comprises: a first closed circuit in which cooling air cooled after being extracted from a combustor plenum is allowed to pass through stationary blades successively to cool the stationary blades, and then recovered and returned to a compressor on the upstream side of the combustor plenum; and a second closed circuit in which cooling air cooled after being extracted from the combustor plenum is allowed to pass through moving blades successively to cool the moving blades, and then recovered and returned to the compressor.

대표
청구항

[ We claim:] [1.] A gas turbine comprising: a compressor;a combustor plenum downstream of said compressor;stationary and moving blades;a cooling air cooler;first and second closed cooling circuits which extract cooling air from said combustor plenum and pass the cooling air through said cooler, the first closed circuit supplying cooling air from said cooler successively through said stationary blades to cool said stationary blades and then recovering the cooling air and returning the cooling air to said compressor, and the second closed circuit supplying...

이 특허를 인용한 특허 피인용횟수: 70

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