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특허 상세정보

Cooled cooling air system for a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-006/08    F02C-007/18    F02C-007/143    F02C-009/18   
출원번호 US-0714554 (2015-05-18)
등록번호 US-10100739 (2018-10-16)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 59
초록

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least ...

대표
청구항

1. A gas turbine engine comprising: a compressor section;a combustor fluidly connected to the compressor section via a primary flowpath;a turbine section fluidly connected to the combustor via the primary flowpath;a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed;the cascading cooling system including at least a first heat exch...

이 특허에 인용된 특허 (59)

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