$\require{mediawiki-texvc}$
  • 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

Aircraft nacelle ventilation and engine exhaust nozzle cooling

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/12    F02K-003/04   
미국특허분류(USC) 60/2261 ; 60/266 ; 239/1273
출원번호 US-0349843 (1994-12-06)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 46  인용 특허 : 4
초록

This disclosure relates to a system for purging of the nacelle of an aircraft and for cooling the edge pieces of the divergent flap of a gas turbine engine\s two-dimensional exhaust system by use of long tubular air pump with axisymmetric supersonic nozzles, a rectangular mixing chamber for pumping nacelle air with fan discharge air and judiciously flowing the air in separate passageways formed in the double clamshell convergent flap of the exhaust nozzle. This reduces the overall aircraft and weapon system weight, with only a minimum increase in the eng...

대표
청구항

A combined purging and cooling system for the nacelle of an aircraft and the edge pieces of the flap of a two-dimensional exhaust nozzle of a gas turbine engine comprising a double clam shell convergent flap and divergent flap, means defining in said convergent flap a pair of side by side passageways, one of said passageways for conducting fan air and the other of said passageways for conducting nacelle air, pumping means including a tubular manifold member and a plurality of supersonic nozzles in said tubular manifold member in fluid communication with ...

이 특허를 인용한 특허 피인용횟수: 46

  1. Zsurka, Mark. Aerodynamic track fairing for a gas turbine engine fan nacelle. USP20190310240561.
  2. Cowan, Curtis C.; Allore, James P.; Attridge, Paul. Convergent divergent nozzle with edge cooled divergent seals. USP2012068205454.
  3. Kehret, Debora F.; Farah, Jorge I.. Convergent divergent nozzle with slot cooled nozzle liner. USP2010077757477.
  4. Murphy,Michael J.; Cowan,Curtis C.; Paul,Stephen A.; Allore,James P.; Harris,Meggan. Convergent/divergent nozzle with modulated cooling. USP2006047032835.
  5. de Verduzan, Léopold Jean-Marie; Floreani, Maurice; Roche, Jacques André Michel. Cooling system for a gas turbine engine post-combustion jet nozzle. USP2004096792748.
  6. Liang George P. ; Yeager William J. ; Soileau John F.. Ejector extension cooling for exhaust nozzle. USP2001106301877.
  7. Lackey Jesse R. ; Catt Jeffrey A.. Exhaust induced ejector nozzle system and method. USP2001106295805.
  8. Froemming, Kenneth W.; Lerg, Bryan H.. Exhaust nozzle apparatus and method for multi stream aircraft engine. USP2018019863366.
  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. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP2017109784212.
  16. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP2017119822732.
  17. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP2017099771893.
  18. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP20190110174715.
  19. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP20190110174716.
  20. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP2017079701415.
  21. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP20181010087885.
  22. Kohlenberg, Gregory A.; Zamora, Sean P.. Gas turbine engine with axial movable fan variable area nozzle. USP2011128074440.
  23. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2014098844264.
  24. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2013118572947.
  25. Kohlenberg, Gregory A.; Zamora, Sean P.; Schwarz, Frederick M.. Gas turbine engine with fan variable area nozzle for low fan pressure ratio. USP2016119494084.
  26. Kohlenberg, Gregory A.; Zamora, Sean P.; Schwarz, Frederick M.. Gas turbine engine with fan variable area nozzle for low fan pressure ratio. USP20180810047628.
  27. Kohlenberg, Gregory A.; Zamora, Sean P.; Schwarz, Frederick M.. Gas turbine engine with fan variable area nozzle to reduce fan instability. USP20190110167813.
  28. Stern, Alfred M.. Gas turbine engine with variable area fan nozzle bladder system. USP2015049010126.
  29. Cowan, Curtis C.; Farah, Jorge I.. Impingement cooled nozzle liner. USP20181110132181.
  30. Liang George P. ; Soileau John F.. Multi-expansion ejector nozzle with diverging walls. USP2000126164059.
  31. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  32. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  33. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  34. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  35. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  36. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  37. Zysman, Steven H.. Nacelle scoop inlet. USP2015089108737.
  38. Khalid, Syed J.. Positionable ejector member for ejector enhanced boundary layer alleviation. USP2017049630706.
  39. Moraes,Ricardo Ferreira. Turbine component with enhanced stagnation prevention and corner heat distribution. USP2006097104068.
  40. Schwark, Jr., Fred W.; Atassi, Oliver V.; Owen, William D.. Variable area fan nozzle bearing track. USP2013058443586.
  41. Grabowski, Zbigniew M.; Morris, Robert J.; Carmichael, Ray W.. Variable area fan nozzle fan flutter management system. USP2015079074531.
  42. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  43. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  44. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  45. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  46. Curtelin,Raphael; Doussinault,Marc; Lapergue,Guy; Durand,Didier. Ventilation system for a convergent divergent exhaust nozzle. USP2007117296397.