$\require{mediawiki-texvc}$
  • 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

Translating lip aircraft cowling structure adapted for noise reduction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/53B ; 244/53R ; 181/215 ; 181/220
출원번호 US-0343729 (1989-04-27)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 22  인용 특허 : 10
초록

The present invention comprises a cowling structure for a gas turbine aircraft engine which allows the aerodynamic characteristics of the inlet passageway to the engine to be varied in accordance with flight conditions. This structure includes an annular lip portion positioned at the front edge of the cowling defining an aerodynamically sharp contour and which is mounted on a set of support struts constructed for allowing the lip portion to be translated forwardly and backwardly from the forward edge of the cowling. The structure further comprises a mech...

대표
청구항

In a gas turbine engine for an aircraft having an air intake passageway defined by a cowling which functions for directing ambient air into said engine, a variable geometry inlet structure adapted for noise reduction, comprising: an annular lip positioned at the front edge of said cowling for defining an aerodynamically sharp contour along the front edge of said cowling; means for axially translating said lip forwardly from and backwardly to the front edge of said cowling including a set of circumferentially spaced struts for mounting said lip, said stru...

이 특허를 인용한 특허 피인용횟수: 22

  1. McDonough, Michael Patrick; Brown, Keith Towers; Gilzean, Scott. Aircraft engine nacelle with translating inlet cowl. USP2012058181905.
  2. Megerian, Sevan; Clifton, Chandler. Compression ramp boundary layer removal. USP2015069046035.
  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 system providing simulated boundary layer thickness increase. USP2012078209953.
  7. Todorovic, Predrag. Gas-turbine engine with telescope-type air inlet of the engine cowling (nacelle). USP2017089719421.
  8. Kubica Daniel J. ; Solheim John A.. Golf club head. USP200003D422043.
  9. Hall Edward J. ; Meade Joseph P.. Method for reducing turboprop noise. USP1999105961067.
  10. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  11. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  12. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  13. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  14. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  15. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  16. Vauchel, Guy Bernard; Epherre-Iriart, Serge. Removable air intake structure for a turbofan engine nacelle. USP2014068740137.
  17. Gupta, Anurag; Graziosi, Paolo; Mani, Ramani. System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine. USP2003126655632.
  18. Mouton, Herve Jean Albert; Vincent, Thomas Alain Christian. Turbojet nacelle having a removable air intake structure. USP2014128899255.
  19. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  20. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  21. Labrecque, Michel; Couture-Gagnon, Vincent; Ullyott, Richard. Variable geometry inlet system. USP20190310221764.
  22. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.