• 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

Low noise aeroengine inlet system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/042    F02C-007/045    F01D-017/14   
출원번호 US-0463077 (2014-08-19)
등록번호 US-9951690 (2018-04-24)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Norton Rose Fulbright Canada LLP
인용정보 피인용 횟수 : 0  인용 특허 : 26

An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through the inlet ...


1. A compressor inlet for an aeroengine, the compressor inlet comprising: an inlet duct for directing an air flow to a compressor of the aeroengine, and at least one deformable wall providing a portion of at least one peripheral wall of the inlet duct and deformable between an undeployed and a deployed position, the at least one deformable wall having a first surface exposed to the air flow and a second surface opposite to the first surface, a plurality of acoustic cells being attached to the second surface of the at least one deformable wall, the at lea...

이 특허에 인용된 특허 (26)

  1. Krojer Hubert (Kippenhausen DT). Air intake with deflecting device against foreign objects impinging in the initial direction of air flow at engine nacel. USP1977094047911.
  2. Hogeboom William H. ; Bielak Gerald W.. Aircraft engine acoustic liner. USP1998075782082.
  3. Porte, Alain; Batard, Herv?. Aircraft engine pod with acoustic attenuation. USP2005056896099.
  4. Schwarz, Frederick M.. Aircraft thermal management system with reduced exhaust re-ingestion. USP2010127857257.
  5. Raimbault, Vincent; Cormerais, Mickael; Champion, Arnaud. Anti-noise device for the air intake conduit of a supercharged internal combustion engine. USP2012108276707.
  6. Dougherty Robert P. (Bellevue WA). Apparatus and method for reducing noise emissions from a gas turbine engine inlet. USP1997125702231.
  7. Frustie, Valerie; Duprieu, Bernard; Gantie, Fabrice. Coating for acoustic treatment integrating the function of frost treatment with hot air. USP2011057938224.
  8. Arnold Michael J. (Bangor GB5). Composite structural component. USP1994055315820.
  9. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  10. Ball William H. (Mercer Island WA). Flush inlet for supersonic aircraft. USP1984084463772.
  11. Flatman Richard J. (Derby GB2). Gas turbine engine. USP1989114881367.
  12. Prasad, Dilip; Feng, Jinzhang; Sabnis, Jayant S.. Gas turbine engine inlet with noise reduction features. USP2012108286654.
  13. Chee Wan T. (Bellevue WA). Inlet cowl attachment for jet engine. USP1985084534167.
  14. Sanders,Bobby W.; Weir,Lois J.. Low sonic boom inlet for supersonic aircraft. USP2006057048229.
  15. Moe, Jeffrey W.; Wunsch, John J.; Sperling, Michael S.. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip. USP2009097588212.
  16. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2000076089505.
  17. Wilson, Robert Samuel. Noise attenuation panel. USP2003086609592.
  18. Farquhar Bannister W. (Bellevue WA) Sloan Denis (Bellevue WA). Noise suppression refracting inlet for jet engines. USP1980034192336.
  19. Derue Anicet (Aix-en-Provence FR). Ram air intakes of rotary-wing aircraft turbine engines. USP1976123998048.
  20. Ayle, Earl; Burchett, Rickey L.. Splicing of curved acoustic honeycomb. USP2013118579076.
  21. Norris Richard M. (Stratford CT) Murphy Joseph P. (Newtown CT). Swinging door particle separator and deicing system. USP1981024250703.
  22. Dhoore Louis G. (Seattle WA) Schultz William H. (Bellevue WA). Turbofan engine having variable geometry fan duct. USP1979054155221.
  23. Tedstone, Donald J.. Vane fairing for inertial separator. USP1982084346860.
  24. Sargisson ; Donald Farley. Variable area inlet for a gas turbine engine. USP1978024075833.
  25. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.
  26. Kechely,Roy Eric. Variable fluid intake with ramp and inflatable bag. USP2008097429018.