• 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

Integral suction device with acoustic panel

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/208;
출원번호 US-0768115 (2010-04-27)
등록번호 US-8459597 (2013-06-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 10  인용 특허 : 27

An inlet flow control system disposed within a nacelle includes a panel on an inner surface of that nacelle. The panel includes a noise attenuation layer that dissipates noise energy. A vacuum source generates a pressure differential across the noise attenuation layer for drawing airflow through the panel and away from an inner surface of the nacelle.


1. A method for preventing separation of air flow from an inner surface of a nacelle for a gas turbine engine comprising the steps of: communicating air along the inner surface of the nacelle with a noise attenuation structure, wherein the noise attenuation structure comprises a face sheet including a plurality of openings communicating with a plurality of cells with uninterrupted solid walls, and a back sheet supporting the plurality of cells and including a plurality of openings in communication with the plurality of cells;generating a pressure differe...

이 특허에 인용된 특허 (27)

  1. Rolston Stephen C.,GBX ; Ashford Edward M.,GB5. Aerodynamic low drag structure. USP1998045743488.
  2. Davison Samuel H. (Milford OH). Aircraft engine starter integrated boundary bleed system. USP1992085136837.
  3. Dougherty Robert P. (Bellevue WA). Apparatus and method for reducing noise emissions from a gas turbine engine inlet. USP1997125702231.
  4. McCaughan John A. I.,GB5. Boundary layer control in aerodynamic low drag structures. USP1998045743493.
  5. Khalid Syed J. (Palm Beach Gardens FL) Robideau Brian A. (Palm Beach Gardens FL). Compressor bleed port. USP1991105059093.
  6. Robert A. Ress, Jr. ; Jeffrey L. Hansen. Compressor endwall bleed system. USP2002086428271.
  7. Lair, Jean-Pierre. Confluent exhaust nozzle. USP2005126971229.
  8. Sanderson John J. (Oakville CAX) Banks Ivor (Georgetown CAX). Controlled bypass inlet duct. USP1990114972672.
  9. Martin Anthony N. (Simsbury CT). Detecting and controlling supersonic airflow normal shock pattern position in an aircraft jet engine assembly. USP1995085437151.
  10. Jaw Link C. (Tempe AZ). Engine stall and distortion suppression system. USP1996095557917.
  11. Beauchamp Edward D. (Lakewood CA) Denk Joseph (Manhattan Beach CA) Murry Roger P. (San Pedro CA). Floating speed electrically driven suction system. USP1996075535967.
  12. Lahti Daniel J. (Cincinnati OH) Yates David E. (Cincinnati OH) Mungur Parmanand (West Chester OH) Stockman Norbert O. (Batavia OH). Hybrid laminar flow nacelle. USP1991024993663.
  13. Cuthbertson Robert D. (Kirkland WA) Schaut Larry A. (Seattle WA). Inlet guide vane bleed system. USP1979054156344.
  14. Koncsek Joseph L. ; Marrs Kenneth J.. Internal compression supersonic engine inlet. USP1999105971000.
  15. Williams, Stewart W; Turner, Brian J. Laminar flow control system and suction panel for use therewith. USP2004066752358.
  16. Meyer,Pascal J. Laminar flow nacelle for an aircraft engine. USP2006057048230.
  17. Tindell Runyon H. ; Parente Charles A.. Low drag inlet design using injected duct flow. USP1999085934611.
  18. Koncsek, Joseph L.; McMahon, Steven L.; Bultman, Myron L.; Sangwin, Michael L.. Method and apparatus for controlling aircraft inlet air flow. USP2003106634595.
  19. Mullender Andrew J. (Nottingham GB2) Rodgers Leonard J. (Derby GB2). Method of manufacturing a porous material. USP1997045618363.
  20. Harris Alfred W. (Bellevue WA). Noise reducing air inlet for gas turbine engines. USP1980124240250.
  21. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2005096942181.
  22. Horstman Raymond H. (Auburn WA). Perforated wing panel with variable porosity. USP1993115263667.
  23. Mathews Douglas C. (Marlborough CT) Peracchio Aldo A. (South Windsor CT). Sound absorbing structure for a gas turbine engine. USP1984064452335.
  24. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.
  25. Rose Philip M. (Chula Vista CA) Mikolajczak Alojzy A. (Coronado CA). Turbofan duct with noise suppression and boundary layer control. USP1988064749150.
  26. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.
  27. Gonidec Patrick,FRX ; Le Docte Thierry Jacques Albert,FRX ; Vauchel Guy Bernard,FRX. Ventilated honeycomb cell sandwich panel and ventilation process for such a panel. USP2000096122892.