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특허 상세정보

Nacelle compartment plenum for bleed air flow delivery system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F03B-015/06    F02C-009/18   
미국특허분류(USC) 415/145; 415/220; 415/914
출원번호 US-0754455 (2007-05-29)
등록번호 US-8657567 (2014-02-25)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, PC
인용정보 피인용 횟수 : 2  인용 특허 : 20

A gas turbine engine is provided with a nacelle having a hollow inner space. The inner space is utilized as a plenum for directing air from an inlet to an outlet at the upstream end of the nacelle to allow control of an effective lip width of the nacelle under certain flight conditions.


1. A gas turbine engine comprising: a nacelle defining an interior space;a fan section, a compressor section and a turbine section positioned within said nacelle, an inner cowl surrounding said compressor section and said turbine section, and said fan section delivering air to said compressor section, and bypass air between said cowl and an interior surface of said nacelle;an air inlet for capturing air and communicating the air into the interior space of said nacelle, said interior space defining a plenum, the air leaving said air inlet, flowing through...

이 특허에 인용된 특허 (20)

  1. Shmilovich, Arvin; Yadlin, Yoram; Smith, David M.; Clark, Roger W.. Active system for wide area suppression of engine vortex. USP2004076763651.
  2. Surply, Thierry; Prat, Damien; Gagnaire, Benoit. Air inlet for commercial aircraft jet engine nacelle. USP2004036708711.
  3. Coffinberry George A. (West Chester OH). Aircraft engine electrically powered boundary layer bleed system. USP1992055114103.
  4. Ball William H. (Mercer Island WA) Syberg Jan (Kent WA). Apparatus for re-energizing boundary layer air. USP1988064749151.
  5. Dale Bradley Elliott ; Peter Nicholas Szucs ; Nicholas Damlis ; Kenneth Paul Onderko. Bifurcated splitter for variable bleed flow. USP2002086438941.
  6. Tindell Runyon H. (Old Bethpage NY). Blown boundary layer control system for a jet aircraft. USP1995095447283.
  7. Parente Charles A.. Combined acoustic and anti-ice engine inlet liner. USP1998115841079.
  8. Koncsek Joseph L. (Seattle WA) McMahon Steven L. (Lake Stevens WA). Ducted boundary layer diverter. USP1996025490644.
  9. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  10. Linton, Alan. Ice protection system. USP2005026848656.
  11. Sheoran Yogendra Y.. Inlet vortex bustor and ice protector for auxiliary power units. USP2001076264137.
  12. Bower Charles R. (Middletown CT) Fowler Frank L. (Guilford CT). Load sharing for engine nacelle. USP1987044658579.
  13. Tindell Runyon H. ; Parente Charles A.. Low drag inlet design using injected duct flow. USP1999085934611.
  14. Maier Mark S. (West Palm Beach FL) Gamble Eric J. (Jupiter FL) Wilson Jack W. (West Palm Beach FL) Calzadilla Eliott L. (North Palm Beach FL) Goetz Gerald F. (Seattle WA). Nacelle air pump for vector nozzles for aircraft. USP1997015593112.
  15. Birbragher Fernando (Miami FL). Nacelle anti-icing system. USP1988044738416.
  16. Aitchison, Paul Archibald; Germain, Patrick David; Smith, Henry. Normally open reverse flow flapper valve. USP2005026851255.
  17. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2003116651929.
  18. Lair, Jean-Pierre. Recessed engine nacelle. USP2005096945031.
  19. Rosenthal Herman Allen. Swirl anti-ice system. USP199906RE36215.
  20. Lindner Ernst (Tubingen DEX) Trittler Guido W. (Unterschleissheim DEX) Britz Klaus (Olching DEX). Turbofan engine with means to smooth intake air. USP1996105568724.