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특허 상세정보

Compressor tip injector

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F04D-029/52    B64D-013/06    F04D-019/00    F04D-027/00    F04D-029/32    F04D-029/68    B64C-021/04    B64D-013/02    B64D-013/04    F16H-015/38    F16H-037/08    F04D-025/02    F04D-027/02    B64D-033/02   
출원번호 US-0136409 (2016-04-22)
등록번호 US-10145387 (2018-12-04)
우선권정보 GB-1508545.9 (2015-05-19)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Oliff PLC
인용정보 피인용 횟수 : 0  인용 특허 : 19
초록

A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compress...

대표
청구항

1. A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system, the compressor tip injector system comprising a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system, the compressor case comprising one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as th...

이 특허에 인용된 특허 (19)

  1. Saiz Manuel Munoz,ESXITX 28017. Aircraft air conditioner energy recovery device. USP2000106128896.
  2. Saiz Manuel Munoz,ESX. Aircraft air conditioner energy recovery method. USP2001096289665.
  3. Davison Samuel H. (Milford OH). Aircraft engine starter integrated boundary bleed system. USP1992085136837.
  4. Goi, Tatsuhiko; Tanaka, Kenichiro; Watanabe, Koji. Aircraft starter generator. USP2013088500583.
  5. Friedrich Helmut (Bremen DT). Apparatus for starting aircraft engines and for operating auxiliary on-board power generating equipment. USP1976063965673.
  6. Williams, Darrell R.. Compressor inlet guide vane de-ice control system and method. USP2010077762081.
  7. Hipsky, Harold W.; DeFrancesco, Gregory L.. Engine driven-shaft driven compressor utilizing infinitely variable transmission. USP2017109796477.
  8. Cloft, Thomas G.; Wall, Sarah M.. Flow distribution system for inlet flow control. USP2010057708230.
  9. Maguire, Alan R; Whellens, Matthew W; Knight, Glenn A. Gas feed assembly. USP2011098011904.
  10. Youssef, Nashed. Gas turbine aircraft engine with power variability. USP2012058181442.
  11. Coffinberry George A. (West Chester OH). Gas turbine engine powered aircraft environmental control system and boundary layer bleed. USP1992095143329.
  12. Rudolph Peter K. C. (Seattle WA). High taper wing tip extension. USP1991085039032.
  13. Christoff William J. (Thousand Oaks CA). Integrated auxiliary power and environmental control unit. USP1985054514976.
  14. Quick David C. (Rockford IL) Wood Allen A. (Beloit WI) Grennan Robert (Rockford IL). Integrated variable speed compressor drive system. USP1992065125806.
  15. Barkowsky, Jan; Dittmar, Jan. Main engine start by means of an aircraft air conditioning system. USP2014098844296.
  16. Stevens Eloy C. (Indianapolis IN) Swain Kenneth (Lizton IN). Method of controlling turbomachine blade flutter. USP1979124178667.
  17. Birbragher Fernando (Miami FL). Nacelle anti-icing system. USP1988044738416.
  18. Bertolotti,Fabio P.. Perforated skin structure for laminar-flow systems. USP2006127152829.
  19. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.