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특허 상세정보

Wet active chevron nozzle for controllable jet noise reduction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/00   
미국특허분류(USC) 060/770; 239/26539; 060/0395; 060/231; 181/213
출원번호 US-0536790 (2006-09-29)
등록번호 US8015819 (2011-08-30)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Robin W., Edwards
인용정보 피인용 횟수 : 3  인용 특허 : 30
초록

Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to pr...

대표
청구항

Having thus set forth the nature of the invention, what is claimed herein is: 1. A jet noise reduction system for use with a jet engine, said jet engine having a first nozzle with a trailing edge, said system comprising:a fluid supply;an injector operably coupled to an orifice proximate to the trailing edge of the first nozzle;said jet noise reduction system having at least a first configuration in which said fluid supply is in fluid communication with said injector and said orifice to thereby direct a stream of fluid with a momentum into a first flow st...

이 특허에 인용된 특허 (30)

  1. Tse, Man-Chun. Aero-engine exhaust jet noise reduction assembly. USP2003116640537.
  2. Allan Barry D. (Huntsville AL). Afterburning reduction. USP1986124630683.
  3. Dorris ; III John ; Smith David Michael ; Parekh David Espineli ; Kibens Valdis. Apparatus and methods for active flow control of a nozzle exhaust plume. USP2001106308898.
  4. Brice,David C.; Whitmire,Julia K.; Barton, deceased,Brian E.. Apparatus, method and system for gas turbine engine noise reduction. USP2007017159383.
  5. John F. Brausch ; Bangalore A. Janardan ; John W. Barter, IV ; Gregory E. Hoff. Chevron exhaust nozzle for a gas turbine engine. USP2002036360528.
  6. Hebert, Leonard J.. Convergent/divergent segmented exhaust nozzle. USP2003126658839.
  7. Hebert, Leonard J.. Convergent/divergent segmented exhaust nozzle. USP2004126826901.
  8. Madden William M. (Palm Springs FL). Cooling liner for an exhaust nozzle. USP1976093979065.
  9. Bonnet,Jean Paul; Delville,Joel; Collin,Erwan; Tensi,Jean; Moreau,Eric; Touchard,Gerard. Device for controlling propulsive jet mixing for aircraft jet engines. USP2007027174718.
  10. Liang George P. ; Yeager William J. ; Soileau John F.. Ejector extension cooling for exhaust nozzle. USP2001106301877.
  11. John Michael Koshoffer. Fluidic nozzle control system. USP2002016336319.
  12. Giffin, III, Rollin George. Gas turbine engine fan. USP2003126662546.
  13. Steven H. Zysman ; Wesley K. Lord ; Gregory A. Kohlenberg. Gas turbine engine jet noise suppressor. USP2002126487848.
  14. Shaw ; Jr. Leonard L. (Troy OH). Jet noise suppressor and method. USP1992035092425.
  15. Martens,Steven; Saddoughi,Seyed Gholamali; Early,Kevin Sean. Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air. USP2006067055329.
  16. Gutmark,Ephraim Jeff; Callender,Bryan W.; Martens,Steven. Method and apparatus for operating gas turbine engines. USP2008087412832.
  17. Catt Jeffrey Alan ; Miller Daniel Nicholas. Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow. USP2000096112513.
  18. Miller Daniel Nicholas ; Catt Jeffrey Alan. Method and apparatus of pulsed injection for improved nozzle flow control. USP2000096112512.
  19. Gowda,Srinivasa Range; Early,Kevin Sean; Martens,Steven. Methods and apparatus for operating gas turbine engines. USP2006087093423.
  20. Gutmark,Ephraim Jeff; Martens,Steven. Methods and apparatus for operating gas turbine engines. USP2007077246481.
  21. Kinzie Kevin W.. Methods and apparatus for suppressing engine test cell howl. USP2000076092621.
  22. Vuillamy Didier (Quincampoix FRX) Baudart Pierre-Andr (Vernon FRX) Tiret Etienne (La Chapelle Reanville FRX) Beaurain Andr (Chambly FRX). Rocket engine nozzle having a notched diverging portion. USP1995095450720.
  23. Balzer, Ronald L.. Segmented mixing device having chevrons for exhaust noise reduction in jet engines. USP2003096612106.
  24. Reba, Ramons Andris; Wake, Brian Ernest; Narayanan, Satish; Maeder, Thierry. Serrated nozzle trailing edge for exhaust noise suppression. USP2009067543452.
  25. White Pritchard H. (Santa Monica CA) De Young Eugene C. (Upland CA). Sound suppressor apparatus. USP1979094168763.
  26. Johnson James E. (Hamilton OH). Spillage drag and infrared reducing flade engine. USP1995045404713.
  27. Renggli,Bernard James. Split shroud exhaust nozzle. USP2007027174704.
  28. Cowan ; Sr. Howard H. (3315 N. Godfrey #36 Midland TX 79707). System for suppressing engine exhaust noise. USP1995075428954.
  29. Mathews Douglas C. ; Low John K. C.. Tabbed nozzle for jet noise suppression. USP2001116314721.
  30. Lillibridge Robert W. ; McGuire Kenneth R. ; Phillips Edward J. ; Matthews Eugene James. Turbofan engine with reduced noise. USP1998015706651.