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특허 상세정보

Two-spool variable cycle engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/06   
미국특허분류(USC) 60/204 ; 60/226R ; 60/262 ; 415/78
출원번호 US-0679097 (1976-04-22)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 51  인용 특허 : 0
초록

An auxiliary fan is disposed upon the periphery of at least a portion of the fan of a conventional gas turbofan engine. Flow modulating components such as variable vanes and nozzles are utilized in conjunction therewith to produce a wide range of operating bypass ratios. Such an engine is one of the variable cycle variety and has the capability of operating efficiently at both subsonic and supersonic speeds.

대표
청구항

A variable cycle gas turbofan engine comprising: a core engine including a compressor, a combustor and a core turbine; a stage or rotatable fan blades for pressurizing a motive fluid, a first portion of which enters said core engine and is discharged therefrom in a hot gas stream, and a second portion of which passes as a bypass stream through a first substantially annular duct generally surrounding said core engine; auxiliary compression means comprising a radial extension of said fan blades for pressurizing an auxiliary motive fluid stream; means for m...

이 특허를 인용한 특허 피인용횟수: 51

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  10. Sheridan, William G.. Dual fan gas turbine engine and gear train. USP20181210151248.
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  12. Sheridan, William G.. Epicyclic gear train for turbo fan engine. USP2012068205432.
  13. Froemming, Kenneth W.; Lerg, Bryan H.. Exhaust nozzle apparatus and method for multi stream aircraft engine. USP2018019863366.
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  15. Lariviere, Erin Lee; Ettorre, Stephen Michael. Flade discharge in 2-D exhaust nozzle. USP2015038984891.
  16. Johnson,James Edward. Flade gas turbine engine with fixed geometry inlet. USP2008077395657.
  17. Johnson,James Edward. Fladed supersonic missile turbojet. USP2009017475545.
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  20. Roberge, Gary D.; Suciu, Gabriel L.. Gas turbine engine systems involving tip fans. USP2013118590286.
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