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특허 상세정보

Device for bleeding off and cooling hot air in an aircraft engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-006/08    F02K-003/04   
미국특허분류(USC) 60/226.1 ; 60/039.07
출원번호 US-0647063 (1996-05-09)
우선권정보 FR-0005703 (1995-05-15)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Watson Cole Stevens Davis, P.L.L.C.
인용정보 피인용 횟수 : 42  인용 특허 : 6
초록

According to the invention, said heat exchanger (18) is arranged at the forward part (13A) of the engine (1) support pylon (13), being traversed by said air stream (21) which leaves the fan (6) and is not directed toward the compressors (3).

대표
청구항

[ I claim:] [1.] A device for bleeding off and cooling hot air in an engine of an aircraft, the aircraft having a body, said engine comprising:an engine body having a compressor, a combustion chamber and a turbine, the engine defining an upstream direction and a downstream direction;a fan arranged in the upstream direction from the engine body, for causing a flow of cold air in the downstream direction;a fairing assembly comprising an air intake, a fan shroud and outer and inner fairings;linking means for connecting the engine body and the fan shroud; an...

이 특허를 인용한 특허 피인용횟수: 42

  1. Stretton, Richard G.. Aeroengine ventilation system. USP2011017861513.
  2. Marini, Remo; Germain, Patrick; Vrljes, Ljubisa. Air cooler system for gas turbine engines. USP20180910072577.
  3. Marini, Remo; Germain, Patrick; Vrljes, Ljubisa. Air cooler system for gas turbine engines. USP2016079388739.
  4. Schwarz, Frederick M.; Elsaesser, Frederick L.. Air-oil heat exchanger. USP2013098534043.
  5. Barbara, Olivier; Antoine, Nicolas. Aircraft air conditioning system. USP2014128915777.
  6. Tretow, Paul R.; Willie, Robert Henry; Robinson, Donald Edwin. Angled inlet system for a precooler. USP2017119810147.
  7. Bagnall,Adam M; Freeman,Christopher. Arrangement for bleeding the boundary layer from an aircraft engine. USP2007047200999.
  8. Beecroft, Peter; Stretton, Richard Geoffrey; Woodrow, Philip Geoffrey; Baralon, Stephane Michel Marcel; Smith, Angus Roy. Bifurcation fairing. USP2017099771873.
  9. Sennoun, Mohammed El Hacin. Bleed air and hot section component cooling air system and method. USP2015129222411.
  10. Appleby, Andrew; Kesner, Charles E.; Garrod, Todd C.; LaBenz, Joel E.. Bleed valve outlet flow deflector. USP2010097797945.
  11. Appleby,Andrew; Kincheloe,Todd A.; Facinelli,William A.; Reed,William H.. Bleed valve outlet flow deflector. USP2008067387489.
  12. Suciu, Gabriel L.; Marry, Brian D.; McCune, Michael E.; Dye, Christopher M.. Compartment cooling for a gas turbine engine. USP2015129200569.
  13. Thomassin, Jean; Bolduc, Sebastien; Villeneuve, Bruno; Berube, Stephane; Fontaine, Mike; Gagnon-Martin, David; Bilodeau, Jade; Julien, Andre; Legare, Pierre-Yves; Nichols, Jason. Compound engine assembly with coaxial compressor and offset turbine section. USP2018049932892.
  14. Thomassin, Jean; Bolduc, Sebastien; Villeneuve, Bruno; Berube, Stephane; Fontaine, Mike; Gagnon-Martin, David; Julien, Andre; Cunningham, Mark; Lafortune, Serge; Legare, Pierre-Yves. Compound engine assembly with common inlet. USP2017109797297.
  15. Thomassin, Jean; Bolduc, Sebastien; Villeneuve, Bruno; Berube, Stephane; Fontaine, Mike; Gagnon-Martin, David; Julien, Andre; Cunningham, Mark; Lafortune, Serge; Legare, Pierre-Yves. Compound engine assembly with modulated flow. USP2018029896998.
  16. Porte, Alain; Prat, Damien. Dual flow turbine engine equipped with a precooler. USP2012038141337.
  17. Porte, Alain; Prat, Damien. Dual flow turbine engine equipped with a precooler. USP2012088250852.
  18. Willie, Robert Henry; Tretow, Paul R.. Dual inlets for a turbofan precooler. USP2017109803546.
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  21. Snyder, Douglas J.. Gas turbine engine and heat exchange system. USP2014128910465.
  22. Baltas, Constantine. Gas turbine engine bifurcation located fan variable area nozzle. USP2018029885313.
  23. Coffinberry, George Albert. Gas turbine engine fan bleed heat exchanger system. USP2012098266889.
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  25. Stretton, Richard G; Richards, Martyn. Heat exchanger arrangement. USP2010107810312.
  26. Duesler, Paul W.; Schwarz, Frederick M.. Heat exchanger for cooled cooling air with adjustable damper. USP20190410253695.
  27. Duesler, Paul W.; Schwarz, Frederick M.. Heat exchanger suspension system with pipe-to-linkage spring rate ratio. USP20181210151247.
  28. Marche, Herve. Heat exchanger, propulsion unit, and aircraft comprising such a propulsion unit. USP2010117823624.
  29. Pollard, Berwyn Owain; Scott, David Russell. Heat exhanger apparatus including heat transfer surfaces. USP2016029260191.
  30. Roberge, Gary D.. Integrated heat exchangers for low fan pressure ratio geared turbofan. USP2018049945325.
  31. Olver, Bryan W.. Low profile bleed air cooler. USP2011017862293.
  32. Czachor,Robert P.. Methods and apparatus for exchanging heat. USP2007037185483.
  33. Coffinberry, George Albert. Methods and apparatus for supplying cooling air to turbine engines. USP2003066578362.
  34. Le Docte, Thierry Jacques Albert. Nacelle with an adaptable outlet section. USP2014118875518.
  35. Martinou, Jean-Marc; Marche, Herve. Propulsion unit for aircraft with heat exchanger having front inlet faces for cooling air flow and hot air flow. USP2013098522529.
  36. Khan, Wasif. Reflex annular vent nozzle. USP2016059347397.
  37. Kraft, Robert Eugene; Gibbens, Nelson Dirk; Hetico, Rolf Robert; Groll, William Charles; Bailey, William Andrew; Stoker, James Edward. Shrouded turbofan bleed duct. USP2009107607308.
  38. Richardson, John. System and method for cooling an aircraft wing. USP2016099452841.
  39. Bintz, Matthew E.; Gendrich, Charles P.; DiTomasso, John C.; Murphy, Andrew J.. Thermal management system for a gas turbine engine with an integral oil tank and heat exchanger in the nacelle. USP20190310233841.
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  41. Marche, Herve. Turbojet engine for aircraft, propulsion unit comprising such a turbojet engine and aircraft comprising such a propulsion unit. USP2011087997061.
  42. Fishler, Benjamin E.. Variable bleed slot in centrifugal impeller. USP2017099752587.