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특허 상세정보

Aircraft scoop ejector nozzle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B63H-025/46   
미국특허분류(USC) 239/265.17 ; 239/265.13 ; 239/265.37 ; 60/242 ; 60/262 ; 60/271
출원번호 US-0807547 (1997-02-28)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Christensen O'Connor Johnson & Kindness PLLC
인용정보 피인용 횟수 : 21  인용 특허 : 0
초록

An engine exhaust nozzle (36) is provided for reducing exhaust noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of scoop ejectors (38) placed equal distances about the circumference of a nozzle outer structure (46). A translatable centerbody (52) is located within the outer structure (46). The annular space between the outer structure (46) and the centerbody (52) define a convergent-divergent exhaust duct (56). Each scoop ejector (38) has a forward inlet (71) and an aft outlet (72). The scoop ejectors are rotata...

대표
청구항

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follow:] [1.] A noise suppression exhaust nozzle for an intermediate bypass ratio aircraft engine, the nozzle comprising:(a) an axisymmetric outer structure having interior sidewalls and a centerbody located within the sidewalls, the area between the centerbody and the sidewalls defining a convergent-divergent exhaust duct for passage of nozzle exhaust;(b) a plurality of scoop ejectors positioned within the nozzle outer structure; each scoop ejector h...

이 특허를 인용한 특허 피인용횟수: 21

  1. John J. Dugan. Apparatus for reducing noise in the jet engine. USP2002086427801.
  2. Rago,Giuseppe. Combined exhaust duct and mixer for a gas turbine engine. USP2006057043898.
  3. Chir, Adam P; Rolt, Andrew M. Cooling system for an aero gas turbine engine. USP2014098833053.
  4. Dussillols, Laurent; Vuillemin, Alexandre Alfred Gaston. Core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft. USP2010107810335.
  5. Thies, Robert. Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air. USP20190110174674.
  6. Alhatim, Omair M.. Exhaust nozzle of a gas turbine engine. USP2016039297334.
  7. Graziosi, Paolo; Kirtley, Kevin; Mani, Ramani. Fluidic chevrons and configurable thermal shield for jet noise reduction. USP2009097581692.
  8. Gibson, Michael E.; Erdmann, James T.. Inlet and exhaust system. USP2014058714919.
  9. Chase, James D.; Garzon, German Andres. Jet nozzle plug with varying, non-circular cross sections. USP2013028371124.
  10. Howe, Mark E.. Method of varying a fan duct nozzle throat area of a gas turbine engine. USP2015028959889.
  11. Pilon, Anthony R.. Noise reduction of supersonic jet engines. USP2013058443931.
  12. Howe, Mark E.. Pivoting fan nozzle nacelle. USP2012038127532.
  13. Guyonnet Xavier Jean Michel Andre,FRX ; Wurniestky Pascal Claude,FRX. Rear mixer ejector for a turbomachine. USP2001016178742.
  14. Cover, Cary L.; Drendel, Albert S.. Rocket thruster assembly comprising load-balanced pintle valve. USP2012078215097.
  15. Cover, Cary L.; Drendel, Albert S.. Rocket thruster comprising load-balanced pintle valve. USP2010127849695.
  16. Todorovic, Predrag; Herzog, Stephan; Seydel, Christian. Scoop of a running-gap control system of an aircraft gas turbine. USP2013048408008.
  17. Alhatim, Omair M.. System of support thrust from wasted exhaust. USP2018019879636.
  18. Leland, Bradley C.; Lundy, Brian F.; Klinge, John D.. System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines. USP2010047690595.
  19. Nyberg, Donald Gerrit; Groudle, Thomas Adrian; Smith, Richard Doyle. Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles. USP2009077565797.
  20. Dussillols, Laurent Christophe; Longeville, Olivier Roland; Vuillemin, Alexandre Alfred Gaston. Variable-section flow mixer for a double-flow turbojet for a supersonic airplane. USP2010117827802.
  21. Blozy,Jack T.; Willard,Charles M.; Messersmith,Nathan L.; Velazquez,Miquel A.. Yaw vectoring for exhaust nozzle. USP2009017481038.