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특허 상세정보

Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/30    F02K-001/28   
미국특허분류(USC) 602/04 ; 602/31 ; 602/71 ; 23/926.517 ; 23/926.519
출원번호 US-0906768 (1997-08-05)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Gray Cary Ware & Freidenrich, LLP
인용정보 피인용 횟수 : 35  인용 특허 : 7

An apparatus and method for varying the effective cross sectional area of an opening through a fixed geometry nozzle provides a fluidic cross flow with an injector incorporated in the throat of the nozzle 68 proximate to the subsonic portion of the flow through the nozzle. One or more injectors 76 are directed at an injector angle opposed to the subsonic portion of the flow. The opposed cross flow from injector 76 interacts with a primary flow 14 through the nozzle 68 to partially block the nozzle's opening 72, thereby effectively decreasing the cross se...


[ What is claimed is:] [23.] A method for vectoring a primary flow through a small area expansion ratio nozzle, comprising the steps of:directing the primary flow through a physical throat of the nozzle wherein the nozzle comprises:an opening for accepting a primary flow through the nozzle;a smooth convergent portion of the nozzle wherein said primary flow is subsonic;a physical throat coupling said converging portion to a diverging portion of the nozzle downstream of said physical throat;at least one primary injector located proximate to said physical t...

이 특허를 인용한 특허 피인용횟수: 35

  1. Lee, Douglas; Anderson, J. Thomas; Hershberger, Brian K.. Apparatus and method for controlling primary fluid flow using secondary fluid flow injection. USP2004016679048.
  2. Spurway Simon Peter,GBX ; Kokkalis Anastasios,GBX. Apparatus for the suppression of infra red emissions from an engine. USP2001106308914.
  3. Berg, Gerald R.; Messersmith, Nathan L.; Lidstone, Gary L.; Hinkey, John. Combustion nozzle fluidic injection assembly. USP2010087775460.
  4. Bonnet,Jean Paul; Delville,Joel; Collin,Erwan; Tensi,Jean; Moreau,Eric; Touchard,Gerard. Device for controlling propulsive jet mixing for aircraft jet engines. USP2007027174718.
  5. Borissov,Anatoli A.. Direct fuel injector assembly for a compressible natural gas engine. USP2008117451942.
  6. Brunet, Edgar; Daris, Thomas; Page, Alain Pierre; Prouteau, Jackie Raymond Julien. Elbow-shaped propulsion gas exhaust assembly in an aircraft. USP2009097581400.
  7. Myers, Gerald A.; Little, David A.. Engine brake for part load CO reduction. USP2011098015826.
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  9. Daris, Thomas; Prouteau, Jackie Raymond Julien; Schenher, Frederic Henri Paul; Brunet, Edgar. Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft. USP2010037681400.
  10. Johnson,James Edward. Fladed supersonic missile turbojet. USP2009017475545.
  11. Truax, Philip P.; Miller, Daniel N.; Ma, Edward C.. Flow control redistribution to mitigate high cycle fatigue. USP2013038402738.
  12. John Michael Koshoffer. Fluidic nozzle control system. USP2002016336319.
  13. Gilbert, David C.. Fluidic vectoring for exhaust nozzle. USP2012018096104.
  14. Kupratis, Daniel B.. Gas turbine engine having core auxiliary duct passage. USP2013028371806.
  15. Miller, Daniel N.; Yagle, Patrick J.; Ginn, Kerry B.; Hamstra, Jeffrey W.. Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle. USP2005116962044.
  16. Efremkin, Artem P.; Efremkin, Pavel V.. Method and device to increase thrust and efficiency of jet engine. USP2011088001762.
  17. Hoffmann, Jürgen; Daxer, Johann Josef; Wippel, Bernhard; Liedtke, Klaus-Dieter. Method for controlling a gas turbine in a power station, and a power station for carrying out the method. USP2014098826670.
  18. Ouellette,Richard P.. Method of operating a pulsejet. USP2006057051510.
  19. Gustafsson, Bernhard; Lundbladh, Anders. Outlet nozzle for a jet engine, an aircraft comprising the outlet nozzle and a method for controlling a gas flow from the jet engine. USP2012128327617.
  20. Ouellette, Richard P.; Kutzmann, Aaron J.. Pulsejet augmentor powered VTOL aircraft. USP2004096793174.
  21. Ouellette, Richard P.. Pulsejet ejector thrust augmentor. USP2005046883304.
  22. Dunbar, Jr.,Donal S.. Retractable afterburner for jet engine. USP2008027334409.
  23. Ouellette, Richard P.; Kutzmann, Aaron J.. Runway-independent omni-role modularity enhancement (ROME) vehicle. USP2005086926235.
  24. Johnson,James Edward. Self powdered missile turbojet. USP2008117448199.
  25. Borissov, Anatoli A.; McCoy, Jr., James J.. Supersonic injector for gaseous fuel engine. USP2004036708905.
  26. Johnson,James Edward. Supersonic missile turbojet engine. USP2008097424805.
  27. Hunter, Louis G.; Miller, Daniel N.; Hagseth, Paul E.. System of pulsed detonation injection for fluid flow control of inlets, nozzles, and lift fans. USP2004076758032.
  28. McCaffrey, Michael G.. Systems and methods involving aerodynamic struts. USP2011108029234.
  29. Page, Alain; Prouteau, Jackie; Daris, Thomas; Doussinault, Marc; Schenher, Frederic. Thrust orienting nozzle. USP2009127631486.
  30. Smith, III, Crawford F.; Bergeron, Steve. Thrust vector system. USP2014088800259.
  31. Johnson,James Edward. Thrust vectoring missile turbojet. USP2009037509797.
  32. Niergarth, Daniel Alan; Prentice, Ian Francis; Kroger, Christopher James. Variable pitch fan blade retention system. USP20181010100653.
  33. Miller, Brandon Wayne; Prentice, Ian Francis; Niergarth, Daniel Alan. Variable pitch fan for gas turbine engine and method of assembling the same. USP20180910072510.
  34. Niergarth, Daniel Alan; Miller, Brandon Wayne; Bradley, Donald Albert. Variable-pitch rotor with remote counterweights. USP2018019869190.
  35. Thomas, Russell H.; Kinzie, Kevin W.. Wet active chevron nozzle for controllable jet noise reduction. USP2011098015819.