$\require{mediawiki-texvc}$
  • 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"
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

Variable contour annular air inlet for an aircraft engine nacelle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-033/02   
미국특허분류(USC) 244/53B ; 244/219 ; 244/130
출원번호 US-0483693 (1990-02-23)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 55  인용 특허 : 5
초록

An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating ...

대표
청구항

In an annular nacelle for a turbine aircraft engine having an annular body with a central axis, a variable contour annular air inlet, comprising: (a) a pair of annular outer and inner surface-defining structures extending axially forwardly from said annular body and being spaced radially from one another with respect to said central axis, said annular outer structure having an annular forward end portion expandable and contractible in diameter; (b) an annular member being disposed between said annular outer and inner structures and coupled to said annula...

이 특허를 인용한 특허 피인용횟수: 55

  1. Chiou, Song; Yu, Jia; Hubert, Claude; Layland, Michael. Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers. USP2010097798285.
  2. Sanicki,Scott; Costa,Mark W.. Acoustic mechanical retainer. USP2007117296656.
  3. Young Kendall G. ; Zimmerman Phil S.. Adaptive control surface apparatus. USP2000126164598.
  4. Devine, Michael Thomas. Adjustable size inlet system. USP20181010107196.
  5. Stretton,Richard G; Beardsley,Peter K; Beaven,David M. Aircraft engine mounting assembly. USP2007117296414.
  6. Botura, Galdemir C.; Flosdorf, David C.. Aircraft engine nacelle ice protection system. USP2010087780117.
  7. Porte, Alain; Fargues, Matthieu; Marro, Martial. Aircraft nacelle comprising a reinforced connection between an air intake and a powerplant. USP2017029567905.
  8. Hendricks, Gavin. Cambered aero-engine inlet. USP2012098261530.
  9. Hendricks, Gavin. Cambered aero-engine inlet. USP2013098528318.
  10. Costa,Mark W.; Brown,Charles W.; Freiler,Chris. Duct liner acoustic splice. USP2007117296655.
  11. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  12. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  13. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  14. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  15. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  16. Mosley, Christopher Alan; Smith, Angus Roy; Sheaf, Christopher Thomas John; Wells, John Richard. Gas turbine engine nacelle. USP2018029885285.
  17. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle. USP2013048418953.
  18. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath. USP2016059328662.
  19. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath and design method thereof. USP2015038985507.
  20. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  21. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  22. Todorovic, Predrag. Gas-turbine engine with telescope-type air inlet of the engine cowling (nacelle). USP2017089719421.
  23. Porte Alain,FRX. Hot air diffuser for a jet engine air inlet cowl with de-icing circuit. USP2000066079670.
  24. Binks, Alan; James, Norman John; Layland, Michael John. Inlet section of an aircraft engine nacelle. USP2016089403599.
  25. Binks, Alan; James, Norman John; Layland, Michael John. Inlet section of an aircraft engine nacelle. USP2012098267642.
  26. Binks, Alan; James, Norman John; Layland, Michael John. Inlet section of an aircraft engine nacelle. USP2012068197191.
  27. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2010087766280.
  28. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2013068459597.
  29. Strunk,John. Integrated inlet attachment. USP2009037503425.
  30. Cloft, Thomas G.; Prihar, Ron I.; Lussier, Darin S.. Integrated inlet fan case. USP2012018092169.
  31. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP2018059957889.
  32. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP2018049951690.
  33. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Low noise aeroengine inlet system. USP20180810054050.
  34. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2001056231006.
  35. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2000076089505.
  36. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2001076260567.
  37. Cox, Brian N.; Davis, Janet B.; dos Santos e Lucato, Sergio Luis; Marshall, David B.; McCabe, Brock S.; Sudre, Olivier H.. Morphable ceramic composite skins and structures for hypersonic flight. USP2009047516918.
  38. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  39. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  40. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  41. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  42. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  43. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  44. Chiou, Song; Yu, Jia; Hubert, Claude; Layland, Michael. Reinforcement members for aircraft propulsion system components configured to address delamination of the inner fixed structure. USP2015049016042.
  45. Parks, Robert. System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control. USP2010127857254.
  46. Vauchel, Guy Bernard; Beilliard, Stephane. Turbojet engine nacelle. USP2014098820344.
  47. Mouton, Herve Jean Albert; Vincent, Thomas Alain Christian. Turbojet nacelle having a removable air intake structure. USP2014128899255.
  48. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  49. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  50. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Variable geometry inlet system. USP20190310221764.
  51. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  52. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  53. Porte, Alain; Prat, Damien. Ventilating air intake arrangement. USP2013048425283.
  54. Costa, Mark W.; Brown, Charles; Foose, Andrew S.. Zero acoustic splice fan case liner. USP2010097797809.
  55. Costa,Mark W.; Brown,Charles; Foose,Andrew S.. Zero acoustic splice fan case liner. USP2008027328771.