$\require{mediawiki-texvc}$
  • 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

Integral suction device with acoustic panel

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/208; 244/209
출원번호 UP-0754518 (2007-05-29)
등록번호 US-7766280 (2010-08-24)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds
인용정보 피인용 횟수 : 26  인용 특허 : 24
초록

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.

대표
청구항

What is claimed is: 1. An inlet flow control system for a nacelle comprising: a panel defining a portion of an interior surface of the nacelle, wherein said panel comprises a noise attenuation layer including a plurality of cells for dissipating noise energy within the nacelle, a face sheet including a plurality of openings for communicating noise energy through to the plurality of cells, and a back sheet supporting the plurality of cells and including openings in communication with the plurality of cells, wherein each of the plurality of cells include ...

이 특허에 인용된 특허 (24)

  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. Beauchamp Edward D. (Lakewood CA) Denk Joseph (Manhattan Beach CA) Murry Roger P. (San Pedro CA). Floating speed electrically driven suction system. USP1996075535967.
  10. 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.
  11. Cuthbertson Robert D. (Kirkland WA) Schaut Larry A. (Seattle WA). Inlet guide vane bleed system. USP1979054156344.
  12. Williams, Stewart W; Turner, Brian J. Laminar flow control system and suction panel for use therewith. USP2004066752358.
  13. Meyer,Pascal J. Laminar flow nacelle for an aircraft engine. USP2006057048230.
  14. Tindell Runyon H. ; Parente Charles A.. Low drag inlet design using injected duct flow. USP1999085934611.
  15. Koncsek, Joseph L.; McMahon, Steven L.; Bultman, Myron L.; Sangwin, Michael L.. Method and apparatus for controlling aircraft inlet air flow. USP2003106634595.
  16. Mullender Andrew J. (Nottingham GB2) Rodgers Leonard J. (Derby GB2). Method of manufacturing a porous material. USP1997045618363.
  17. Harris Alfred W. (Bellevue WA). Noise reducing air inlet for gas turbine engines. USP1980124240250.
  18. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2005096942181.
  19. Horstman Raymond H. (Auburn WA). Perforated wing panel with variable porosity. USP1993115263667.
  20. Mathews Douglas C. (Marlborough CT) Peracchio Aldo A. (South Windsor CT). Sound absorbing structure for a gas turbine engine. USP1984064452335.
  21. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.
  22. Rose Philip M. (Chula Vista CA) Mikolajczak Alojzy A. (Coronado CA). Turbofan duct with noise suppression and boundary layer control. USP1988064749150.
  23. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.
  24. 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.

이 특허를 인용한 특허 피인용횟수: 26

  1. Boulet, Nicolas; Affortit, Sébastien. Air inlet for aircraft propulsion unit having a structure resistant to excess pressure and a process for repairing an air inlet of an aircraft propulsion unit. USP2015069061769.
  2. Namgoong, Howoong. Aircraft engine nacelle. USP20181110131443.
  3. Sawyers-Abbott, Nigel David. Combined inlet laminar and thrust reverser cascade efflux flow control system. USP2018049951719.
  4. Syassen, Freerk. Device for reducing the aerodynamic drag of a leading surface of an aircraft. USP2014108864082.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  9. Kestler, Steven M.; Sundar, Prithvi; Li, Yuan. Method of controlling boundary layer flow. USP2017109789954.
  10. Brown, Keith T.. Modular plenum and duct system for controlling boundary layer airflow. USP2017099758240.
  11. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  12. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  13. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  14. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  15. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  16. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  17. Tiwari, Sean; Weaver, Luby. Perforated surface for suction-type laminar flow control. USP20180610000277.
  18. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element. USP2016039272772.
  19. Huynh, Thuy; Werner, Eric. Variable geometry flush boundary diverter. USP2018019862482.
  20. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.
  21. Walker, James. Variations and methods of producing ventilated structural panels. USP2015069050766.
  22. Walker, James. Ventilated structural panels and method of construction with ventilated structural panels. USP2015079091049.
  23. Walker, James. Ventilated structural panels and method of construction with ventilated structural panels. USP2013128615945.
  24. Walker, James. Ventilated structural panels and method of construction with ventilated structural panels. USP2017039604428.
  25. Walker, James. Ventilated structural panels and method of construction with ventilated structural panels. USP2014018635822.
  26. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift. USP2016039278753.