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특허 상세정보

Turbojet cooling system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-006/18    F02K-011/00    B64B-001/24   
미국특허분류(USC) 60/3907 ; 60/262 ; 60/266 ; 60/3983
출원번호 US-0180396 (1994-01-12)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 35  인용 특허 : 0
초록

The hot core engine compartment of a turbojet engine is cooled by the metered flow of cooling air exhausted through a laminar flow nacelle system. This arrangement reduces the need for extracting bypass ram air from the engine performance cycle for cooling purposes and thereby improves specific fuel consumption and engine efficiency. A turbocompressor pump driven by bleed air from the core engine compressor draws cooling air through the laminar flow nacelle system and pumps the air into a manifold surrounding the core engine.

대표
청구항

A cooling system for a turbojet engine, comprising: nacelle means defining an air inlet leading into said engine, said nacelle means having port means disposed about said inlet for admitting air through said nacelle for promoting laminar flow around said nacelle; duct means disposed within said nacelle and communicating with said port means; a core engine disposed within said turbojet engine: core air inlet means disposed within said nacelle for providing air to said core engine; bypass means for bypassing air from said core air inlet mean around said co...

이 특허를 인용한 특허 피인용횟수: 35

  1. Modafferi, Mario. APU core compressor providing cooler air supply. USP2003066578351.
  2. Beier, Jürgen. Accessory mounting for a gas turbine engine. USP2017029562477.
  3. Rupp, George D.; Troia, Trajaen J.. Aircraft engine airflow modulation apparatus and method for engine bay cooling and cycle flow matching. USP2016059353684.
  4. Suciu, Gabriel L.; Glahn, Jorn A.; Merry, Brian D.; Dye, Christopher M.. Bypass air-pump system within the core engine to provide air for an environmental control system in a gas turbine engine. USP2016079394803.
  5. Suciu, Gabriel L.; Glahn, Jorn A.; Merry, Brian D.; Dye, Christopher M.. Combined pump system for engine TMS AOC reduction and ECS loss elimination. USP2016109470153.
  6. Moniz, Thomas Ory. Compact booster bleed turbofan. USP2009127624581.
  7. Suciu, Gabriel L.; Merry, Brian D.; Glahn, Jorn A.; Dye, Christopher M.. Constant speed pump system for engine ECS loss elimination. USP2015109163562.
  8. Suciu, Gabriel L.; Glahn, Jorn A.; Merry, Brian D.; Dye, Christopher M.. Constant-speed pump system for engine thermal management system AOC reduction and environmental control system loss elimination. USP2015109151224.
  9. Solntsev, Alexander; Bammann, Holger. Cooling air supply for the cooling of different systems requiring cooling air in an aircraft. USP2013128602088.
  10. Laborie Daniel J. ; Mc Nulty Michael. Core compartment valve cooling valve scheduling. USP2001036202403.
  11. Lamb, Jr., Donald William; Simonetti, Joseph Lawrence. Engine inlet. USP2016019234460.
  12. Verseux, Olivier. Fairing device for aircraft propulsion assembly comprising an internal compartment fitted with a fan. USP20180910066551.
  13. Bancalari Eduardo E.. Gas turbine cooling system. USP2001106295803.
  14. Coffinberry, George Albert. Gas turbine engine fan bleed heat exchanger system. USP2012098266889.
  15. Laborie, Daniel Jean-Louis. Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl. USP2010027665310.
  16. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  17. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  18. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  19. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  20. Pritchard, Jr., Byron Andrew; Califf, Charles Daniel; Wood, Peter John; Holm, Raymond Gust; van de Wall, Allan George; Pezzi, Peter Alfred. Gas turbine engine variable bleed valve for ice extraction. USP2018059982598.
  21. Vest Michael S.. Hot air injection for swirling rotational anti-icing system. USP2001076267328.
  22. Suciu, Gabriel L.; Penda, Allan R.; Merry, Brian D.; Dye, Christopher M.; Snape, Nathan. Integrated thermal system for a gas turbine engine. USP2017109797311.
  23. Ellis, Sean Patrick; Stieger, Rory Douglas. Method of controlling a cooling system. USP2017109776727.
  24. Brown, Keith T.. Modular plenum and duct system for controlling boundary layer airflow. USP2017099758240.
  25. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  26. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  27. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  28. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  29. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  30. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  31. Snyder, Douglas J.; Pesyna, Kenneth M.. Ram air thermal management system. USP2017129840967.
  32. Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.. Thermal management system integrated pylon. USP2014098826641.
  33. Campbell, Jr., Christian X.; Marra, John J.; Marsh, Jan H.. Turbine airfoil with ambient cooling system. USP2016069359902.
  34. Brostmeyer, Joseph; Wilson, Jr., Jack W.. Turbine last stage blade with forced vortex driven cooling air. USP2010037677048.
  35. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.