$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Buffer region for the nacelle of a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02    F02C-007/12   
미국특허분류(USC) 60/2261 ; 60/3983
출원번호 US-0300516 (1989-01-23)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 37  인용 특허 : 12
초록

A buffer system for cooling a buffer region 66 in the nacelle 14 of a gas turbine engine 12 after engine shutdown is disclosed. Various construction details are developed for positively providing cooling air after engine operation to the buffer region of the nacelle, such as with a blower means 74. A coolable component 96, 98, 100, is disposed in the region. In one detailed embodiment, a shroud 72 extends about the buffer region and at least a portion of the coolable component is disposed in the shroud.

대표
청구항

A buffer system for the nacelle of a turbofan gas turbine engine, which comprises: a nacelle wall extending circumferentially about the engine having an interior and an exterior, the nacelle wall having an opening in the nacelle wall for flowing air from the exterior of the nacelle to the interior; a buffer region on the interior of the nacelle having a portion of at least one coolable component disposed therein; a passage for buffer air in flow communication with the opening in the nacelle wall and with the buffer region on the interior of the nacelle; ...

이 특허를 인용한 특허 피인용횟수: 37

  1. Laborie Daniel J. ; Mc Nulty Michael. Core compartment valve cooling valve scheduling. USP2001036202403.
  2. Mazeaud, Georges; Yvon, Didier Jean-Louis. Device for supporting and housing auxiliaries in a bypass turbojet. USP2010107805949.
  3. Broughton, Paul; Kennea, Robin Charles. Electrical Harness. USP2018049934885.
  4. Willmot, Michael Christopher; Broughton, Paul; Peace, Richard; Skinner, Gary Alan; Kennea, Robin Charles. Electrical raft assembly. USP2017119826575.
  5. Verseux, Olivier. Fairing device for aircraft propulsion assembly comprising an internal compartment fitted with a fan. USP20180910066551.
  6. Teia Dos Santos Medes Gomes, Luis Daniel; Galindo-Lopez, Carlos Hannover. Flow guiding system and rotary combustion engine. USP2017119816438.
  7. Cazenave,Olivier J F; Sherlock,Robert E.; Clark,Tim A.. Gas turbine engine haveing a disconnect panel for routing pipes and harnesses between a first and a second zone. USP2006037010906.
  8. Laborie, Daniel Jean-Louis. Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl. USP2010027665310.
  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. Broughton, Paul; Peace, Richard; Skinner, Gary Alan; Kennea, Robin Charles. Gas turbine engine systems. USP2017089730275.
  16. Suciu, Gabriel L.; Chandler, Jesse M.. Gas turbine engine with plural accessory air paths. USP20190410247097.
  17. Broughton, Paul; Peace, Richard; Skinner, Gary Alan; Kennea, Robin Charles. Gas turbine part having an electrical system embedded in composite material. USP2017079713202.
  18. Broughton, Paul; Willmot, Michael Christopher; Dalton, Justin Sean. Heated rigid electrical harness for a gas turbine engine. USP2017119814101.
  19. Ouplomb, Patrick. Method and system for feeding and ventilating with air a plant of an aircraft auxiliary power unit. USP2015129205926.
  20. Broughton, Paul; Peace, Richard. Method of servicing a gas turbine engine. USP2016029259808.
  21. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  22. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  23. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  24. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  25. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  26. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  27. Dalton, Justin; Broughton, Paul; Peace, Richard; Skinner, Gary Alan; Kennea, Robin Charles. Rigid raft. USP2016099456472.
  28. Sommerer, Yannick; Jeanmougin, Stéphanie. Thermal protection device for equipment in a turbomachine engine compartment. USP2018049932900.
  29. Leyko, Matthieu; Bertucchi, Jean; Szydlowski, Julien. Turbomachine comprising a device for the cooling of a pylon. USP2017019540109.
  30. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2013038402744.
  31. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2012088240126.
  32. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2013118578716.
  33. Schirtzinger, Gary A.; Wurzbacher, Lance; Orr, Joseph L.. Valve system for a gas turbine engine. USP2012108286416.
  34. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  35. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  36. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  37. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.