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특허 상세정보

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Gas turbine engine cooling supply circuit

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/12   
미국특허분류(USC) 60/3975 ; 415/115
출원번호 US-0313951 (1994-09-28)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 65  인용 특허 : 0
초록
▼

A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow ...

대표
청구항
▼

In a gas turbine engine having an axis of rotation and a compressor driven by a turbine disposed downstream thereof, an apparatus for cooling said turbine comprising: a first cooling air supply circuit comprising: a primary cooling air source providing primary cooling air; means for channelling said primary cooling air from said primary cooling air source to an annular manifold; and means for discharging said primary cooling air from said manifold into a first turbine cavity to cool turbine components in flow communication therewith; and a second cooling...

이 특허를 인용한 특허 피인용횟수: 65

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