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Hybrid laminar flow nacelle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/53B ; 249/53R ; 249/130 ; 249/208
출원번호 US-0359556 (1989-06-01)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 36  인용 특허 : 13
초록
▼

A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between the surfaces and a tailored outer surface geometry shape for producing reduced friction drag laminar flow over the outer cowl at cruise operation of the aircraft and producing separation-free flow over the inner surface of the cowl at off-cruise operation of the...

대표
청구항
▼

A hybrid laminar flow nacelle for housing an engine of an aircraft, comprising: (a) an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at said leading lip; and (b) a suction bleed system including a plurality of air suction elements defined in said outer and inner forward surface portions axially downstream from said leading lip in a direction of airflow, suction generating means, and means interconnecting said air suction elements and suction generating means ...

이 특허에 인용된 특허 (13)

  1. Gratzer Louis B. (Seattle WA) Gillette Walter B. (Issaquah WA). Aerodynamically contoured, low drag wing engine and engine nacelle combination. USP1984054449683.
  2. Gratzer Louis B. (Seattle WA) Gillette Walter B. (Issaquah WA). Aerodynamically contoured, low drag wing, engine and engine nacelle combination. USP1984054449681.
  3. Anxionnaz Rene (8 ; RUE Nicolas Chuquet 75-Paris FR). Device for regulating and recovering the boundary layer over the surface of a body such as an aircraft in flight. USP1976043951360.
  4. Lahti Daniel J. (Cincinnati OH). Drag-reducing nacelle. USP1983104410150.
  5. Yates Ivan R. (Kingston-upon-Thames GB2). Duct means for aircraft. USP1985084533095.
  6. Wynosky Thomas A. (Madison CT). Gas turbine engine nacelle. USP1988024722357.
  7. Tracksdorf Peter (Grbenzell DEX). Jet engine nacelle. USP1989094865268.
  8. Gratzer Louis B. (Seattle WA). Laminar flow control airfoil. USP1989034813631.
  9. Lahti Daniel J. (Cincinnati OH) Younghans James L. (Cincinnati OH). Laminar flow necelle. USP1989014799633.
  10. Lurz Werner (Hamburg DEX). Method for stabilizing laminar separated boundary layers. USP1987054664345.
  11. Dusa Donald J. (Cincinnati OH) Wagenknecht Conrad D. (West Chester OH). Nacelle installation. USP1984084466587.
  12. Miller Brent A. (Olmsted Falls OH). Self stabilizing sonic inlet. USP1979054154256.
  13. Rose Philip M. (Chula Vista CA) Mikolajczak Alojzy A. (Coronado CA). Turbofan duct with noise suppression and boundary layer control. USP1988064749150.

이 특허를 인용한 특허 피인용횟수: 36

  1. Peter May DE. Aircraft airfoil with close-mounted engine and leading edge high lift system. USP2002046364254.
  2. Laurant, Franck; Bellet, Francois; Joret, Jean-Philippe. Composite panel having a built-in duct. USP2016089410485.
  3. Violett, Robert S.. Electric propulsion system useful in jet-type model airplanes and UAVS. USP2011098026644.
  4. Violett, Robert S.. Electric propulsion system useful in jet-type model airplanes and UAVs. USP2012118310117.
  5. Arcas Noe ; Hutto Frederick M. ; Parente Charles A.. Extended reaction acoustic liner for jet engines and the like. USP2000106135238.
  6. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  7. Cloft, Thomas G.; Wall, Sarah M.. Flow distribution system for inlet flow control. USP2010057708230.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  10. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  11. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  12. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  13. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  14. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2010087766280.
  15. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2013068459597.
  16. Blackner Anthony M.. Jet engine and method for reducing jet engine noise by reducing nacelle boundary layer thickness. USP2000086094907.
  17. Koppelman, Henry J.; Gregg, Paul S.. Laminar flow panel. USP2014078783624.
  18. Kestler, Steven M.; Sundar, Prithvi; Li, Yuan. Method of controlling boundary layer flow. USP2017109789954.
  19. Dawson, David Lynn; Lariviere, Erin Lee; Petersen, Brian Joseph; Ellerhorst, Robert Jerome. Multi-nozzle flow diverter for jet engine. USP2018039920710.
  20. Brown, Keith T.; Byrne, Stuart J.; Kestler, Steven M.. Multi-zone active laminar flow control system for an aircraft propulsion system. USP2018039908620.
  21. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  22. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  23. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  24. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  25. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  26. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  27. Brown, Keith T.; Fowler, Frank J.; Byrne, Stuart J.; Stein, Adam. Nacelle inlet with extended outer barrel. USP2018019874228.
  28. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  29. Khidekel, Ann E.. Optimized nacelle profile and plenum shape for boundary layer ingestion active laminar flow control. USP20190110189558.
  30. Booher, Sr., Benjamin V.. Parasitic drag induced boundary layer reduction system and method. USP2017079701399.
  31. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.
  32. Surply, Thierry; Bourdeau, Christophe. Turbojet nacelle and method for controlling separation in a turbojet nacelle. USP2014028640986.
  33. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  34. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  35. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  36. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.

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