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특허 상세정보

Nacelle inlet lip anti-icing with engine oil

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-015/06    B64D-015/00   
미국특허분류(USC) 244/134.R; 244/134.B; 060/039.093
출원번호 US-0628368 (2003-07-29)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Ogilvy Renault LLP
인용정보 피인용 횟수 : 33  인용 특허 : 7
초록

A nacelle for housing a gas turbine engine having a pressurized oil system for lubricating components thereof comprises an inlet lip defining a leading edge of the nacelle, the inlet lip having a conduit therein in fluid flow communication with the pressurized oil system of the gas turbine engine and defining an oil passage for circulation of pressurized engine oil therethrough. The conduit is in heat transfer communication with an outer surface of the inlet lip.

대표
청구항

The invention claimed is: 1. A nacelle for housing a gas turbine engine having a pressurized oil system for lubricating components thereof, said nacelle comprising: an inlet lip defining a leading edge of said nacelle, said inlet lip having a conduit therein in fluid flow communication with said pressurized oil system of said gas turbine engine, said conduit defining an oil passage within which circulates pressurized engine oil therethrough, said conduit being in heat transfer communication with an outer surface of said inlet lip; and a control system t...

이 특허를 인용한 특허 피인용횟수: 33

  1. Johnson, Rick A.; Pham, Victor D.; Gally, Daniel H.; Seydel, Joseph James; Natsui, Edward Charles. Aircraft anti-icing systems having deflector vanes. USP2016119488067.
  2. Epstein, Eran. Airplane leading edge de-icing apparatus. USP2014048702039.
  3. Etling, Keith A.. Anti-icing apparatus for honeycomb structures. USP2011118052089.
  4. Tall, Jr., Michael Thomas; Lund, Brian C.; Huang, Jianming. Anti-icing internal manifold. USP2018039920691.
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  6. Blackwelder, Mark J.; Alt, John Timothy; Gagne, Steven; Vetters, Daniel Kent. Electrical power generation apparatus for contra-rotating open-rotor aircraft propulsion system. USP2012108294316.
  7. Cloft, Thomas G.. Gas turbine engine assembly including accessory components within the nacelle. USP2014078769924.
  8. Lozier, Thomas S.; Bowman, Mark E.; Cathcart, Gregory D.; Porter, Ronald P.. Gas turbine engine duct having a coupled fluid volume. USP2014018627667.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  10. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  11. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  12. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  13. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  14. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  15. Venkataramani, Kattalaicheri Srinivasan; Moniz, Thomas Ory; Stephenson, Justin P.; Bailey, William Andrew. Heat pipe-based cooling apparatus and method for turbine engine. USP2010127845159.
  16. Knott, David S; Lambourne, Alexis; Rolt, Andrew M; Buffone, Cosimo. Heat transfer arrangement for fluid-washed surfaces. USP2014128915058.
  17. Roby, Benjamin; Monttinen, Jarmo. Heated booster splitter plenum. USP2016039279337.
  18. Roby, Benjamin; Monttinen, Jarmo. Heated booster splitter plenum. USP2016049309781.
  19. Goodman, Robert; Zheng, Zhijun; Greenberg, Michael D.. Inline pressure regulating valve assembly with inlet pressure bias. USP2017129849992.
  20. Rocklin, Mark; Karvountzi, Georgia C.; Hummel, Daniel S.. Method and apparatus for aircraft anti-icing. USP2011118061657.
  21. Schilling, Jan Christopher. Method and apparatus for operating gas turbine engines. USP2012068205426.
  22. Mercier, Claude; Collopy, Gary. Nacelle anti-ice valve utilized as compressor stability bleed valve during starting. USP2018019879599.
  23. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  24. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  25. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  26. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  27. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  28. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  29. 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.
  30. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  31. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  32. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  33. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.