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특허 상세정보

Fan nacelle flow control

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 415/001; 415/126; 415/150; 415/159; 415/914; 244/053B; 060/226.1
출원번호 US-0957780 (2007-12-17)
등록번호 US-8529188 (2013-09-10)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds P.C.
인용정보 피인용 횟수 : 9  인용 특허 : 22
초록

This disclosure relates to a gas turbine engine including a core engine that drives a fan. A fan nacelle surrounds the fan and provides an inner surface facing the fan. The fan nacelle includes an inlet lip adjoining the inner surface. A ring is arranged at the inner surface and is axially upstream from the fan. The ring includes a deployed position in which the ring is spaced radially inwardly from the inner surface to provide a gap therebetween through which air flows. The ring also includes a stowed position in which the ring is arranged radially inwa...

대표
청구항

1. A gas turbine engine comprising: a core engine driving a fan;a fan nacelle surrounding the fan and providing an inner surface facing the fan, the fan nacelle including an inlet lip adjoining the inner surface; anda ring arranged at the inner surface axially upstream from the fan, the ring having a deployed position in which the ring is spaced radially inwardly from the inner surface to provide a gap there between through which air flows, and a stowed position in which the ring is arranged radially outwardly from the deployed position and proximate to ...

이 특허에 인용된 특허 (22)

  1. Rolston Stephen C.,GBX ; Ashford Edward M.,GB5. Aerodynamic low drag structure. USP1998045743488.
  2. Surply, Thierry; Prat, Damien; Gagnaire, Benoit. Air inlet for commercial aircraft jet engine nacelle. USP2004036708711.
  3. Sanders Bobby W. ; Weir Lois J.. Axi-symmetric mixed compression inlet with variable geometry centerbody. USP2001086276632.
  4. Welch John M. ; Benton William E. ; Lobsinger Michael R.. Engine nacelle outer cowl panel with integral track fairings. USP2000106129311.
  5. Cowan Samuel Joseph (Seattle WA) Little John William (Bellevue WA). Fluid layer acoustic shield for turbofan jet propulsion engine. USP1977054023644.
  6. Wynosky Thomas A. (Madison CT). Gas turbine engine nacelle. USP1988024722357.
  7. Coffinberry George A. (West Chester OH). Gas turbine engine powered aircraft environmental control system and boundary layer bleed. USP1992095143329.
  8. Adamson ; Arthur P.. Gas turbine engine with recirculating bleed. USP1978044083181.
  9. Lahti Daniel J. (Cincinnati OH) Yates David E. (Cincinnati OH) Mungur Parmanand (West Chester OH) Stockman Norbert O. (Batavia OH). Hybrid laminar flow nacelle. USP1991024993663.
  10. Tracksdorf Peter (Grbenzell DEX). Jet engine nacelle. USP1989094865268.
  11. Sanders,Bobby W.; Weir,Lois J.. Low sonic boom inlet for supersonic aircraft. USP2006057048229.
  12. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2001076260567.
  13. Stockman Norbert O. (Batavia OH) Yates David E. (Cincinnati OH) Crum Timothy S. (Fairfield OH). Nacelle inlet for an aircraft gas turbine engine. USP1991105058617.
  14. Duane C. McCormick ; Wesley K. Lord. Passively driven acoustic jet controlling boundary layers. USP2002046379110.
  15. Sankrithi, Mithra M. K. V.; Nelson, Paul E.. Rotatable scarf inlet for an aircraft engine and method of using the same. USP2004076764043.
  16. Gupta, Anurag; Graziosi, Paolo; Mani, Ramani. System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine. USP2003126655632.
  17. Duane C. McCormick ; Daniel L. Gysling. Tangentially directed acoustic jet controlling boundary layer. USP2002056390418.
  18. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.
  19. Brian E. Barton. Translating independently mounted air inlet system for aircraft turbofan jet engine. USP2002016340135.
  20. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.
  21. Frantz John J. (Fairfield OH). Variable double lip quiet inlet. USP1979014132240.
  22. Miller Robin Mihekun ; Tunkel Roman N.. Vibration-driven acoustic jet controlling boundary layer separation. USP2000086109566.