$\require{mediawiki-texvc}$
  • 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) F02C-007/18   
미국특허분류(USC) 60/204 ; 60/3983
출원번호 US-0584557 (1990-09-18)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 26  인용 특허 : 0
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 method for ventilating the core nacelle compartment of a turbofan gas turbine engine which comprises the steps of: flowing air during engine operative conditions from the exterior of the nacelle into the interior of the nacelle by discharging the air from at least one passage from a first location in the upper region of the nacelle core compartment under most operative conditions of the engine and discharging the air from at least one passage at a second location adjacent the outer case of the engine for impinging cooling air on the exterior of the eng...

이 특허를 인용한 특허 피인용횟수: 26

  1. Porte, Alain; Prat, Damien. Dual flow turbine engine equipped with a precooler. USP2012088250852.
  2. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  3. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  4. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  6. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  7. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  8. Rodgers Joseph H. (Vernon CT) Kasprow Robert F. (Wethersfield CT). Method of operating a gas turbine engine powerplant for an aircraft. USP1996095553449.
  9. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  10. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  11. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  12. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  13. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  14. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  15. Diaz, Carlos Enrique; Laborie, Daniel Jean-Louis; Geary, Stephen Dennis. Thermally actuated passive gas turbine engine compartment venting. USP2015038991191.
  16. Dittmann, Rolf; Hurter, Jonas; Marmilic, Robert; Meylan, Pierre; Pauli, Ernst. Turbomachine. USP2005126978622.
  17. Dittmann,Rolf; Hurter,Jonas; Marmilic,Robert; Meylan,Pierre; Pauli,Ernst. Turbomachine. USP2008027329084.
  18. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2013038402744.
  19. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2012088240126.
  20. Schirtzinger, Gary A.. Valve system for a gas turbine engine. USP2013118578716.
  21. Schirtzinger, Gary A.; Wurzbacher, Lance; Orr, Joseph L.. Valve system for a gas turbine engine. USP2012108286416.
  22. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  23. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  24. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  25. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  26. Wilcox, David E.. Witness drain valve. USP2003066571562.