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특허 상세정보

Turbine engine with intercooler in bypass air passage

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-071/43    F02K-003/00   
미국특허분류(USC) 602/261 ; 602/66 ; 607/28 ; 600/397.5
출원번호 US-0002018 (1997-12-31)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Downs Rachlin & Martin PLLC
인용정보 피인용 횟수 : 41  인용 특허 : 16
초록

A turbine engine (20) having bypass and core passages (30 and 40), a high pressure compressor (80) for compressing air in the core passage and an intercooler (120, 220) for cooling core air (42) in the core passage prior to discharge by the high pressure compressor. The intercooler includes a plurality of heat exchange elements (140) positioned in the bypass passage through which all or a portion of the core air is transported. Heat in the core air is transferred via the heat exchange elements to the relatively cool bypass air, thereby cooling the core a...

대표
청구항

[ What is claimed is:] [1.] A turbine engine that produces thrust, comprising:a. a low pressure compressor:b. a core air passage through which core air flows;c. a high pressure compressor connected to said core air passage, said high pressure compressor having an outlet;d. a bypass air passage through which bypass air flows, said bypass air having less thermal energy than said core air;e. an intercooler connected to said core air passage and extending into said bypass air passage, wherein said intercooler is constructed to transport more than a mass blee...

이 특허에 인용된 특허 (16)

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이 특허를 인용한 특허 피인용횟수: 41

  1. Brault, Michel Gilbert Roland; Rousselin, Stephane; Tantot, Nicolas Jerome Jean; Touret, Roxane Carmelle Jeanne Yvonne. Aeroengine fitted with heat exchanger means. USP2009087568336.
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  7. Kupratis, Daniel Bernard; Hanrahan, Paul R.. Cooled cooling air system for a gas turbine engine. USP20181010100739.
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