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특허 상세정보

Combustion control system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-009/14   
미국특허분류(USC) 60/3923 ; 60/3929 ; 60/3937
출원번호 US-0920191 (1978-06-29)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 33  인용 특허 : 6

A combustion system for gas turbines is disclosed which is capable of burning gaseous and liquid fuels. Excess air injected into the reaction zone of the combustor produces either a fuel-lean or fuel-rich mixture which lowers the temperature at which combustion occurs and thereby reduces the amount of nitrogen oxides in the turbine exhaust. Efficient combustion is maintained across a wide range of turbine loads by means of a control mechanism disposed externally of the combustor, which directs the airflow from the compressor to the reaction zone and to t...


In a gas turbine of the type wherein at least one combustor is coupled to the discharge of the compressor and the fuel is burned with excess air or excess fuel to maintain a low temperature of combustion, said combustor having a substantially tubular configuration and including a combustion liner configured to define an elongate combustion chamber substantially centered about an axis, said combustion chamber terminating in a chamber end wall at one end thereof and including a reaction zone near said chamber end wall and a dilution zone axially spaced fro...

이 특허를 인용한 특허 피인용횟수: 33

  1. Lenertz James E. ; Samuel Philip. Annular combustor tangential injection flame stabilizer. USP2001046220035.
  2. Martling,Vincent C.; Xiao,Zhenhua. Apparatus and method for reducing the heat rate of a gas turbine powerplant. USP2006057047723.
  3. Kolman, Kevin Michael; Storey, James Michael. Bypass air injection method and apparatus for gas turbines. USP2003056568188.
  4. Greenwood Stuart ; Montoya Jorge ; Kelton Mike ; Fahme Tony. Combustion air control system for a gas turbine engine. USP2000076082093.
  5. Romig, Bryan Wesley; Overby, Brandon Taylor. Combustion casing manifold for high pressure air delivery to a fuel nozzle pilot system. USP2016119500367.
  6. Laster, Walter R.; Bandaru, Ramarao V.. Controlled pilot oxidizer for a gas turbine combustor. USP2010077752850.
  7. Mowill R. Jan,NLX. Convectively cooled, single stage, fully premixed controllable fuel/air combustor. USP2001046220034.
  8. Mowill R. Jan (c/o OPRA B.V. Opaalstraat 60-P.O. Box 838 7550 AV Hengelo NLX). Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission. USP1997065638674.
  9. Greeb Kevin. Dynamic control system and method for catalytic combustion process and gas turbine engine utilizing same. USP2000086095793.
  10. Tort-Oropeza Alejandro,MXX. External combustion engine. USP1999105964087.
  11. Sanders,Noel A. Fuel injector. USP2007047200986.
  12. Terazaki,Masao; Kanezawa,Yoshiyuki; Horikawa,Hideto. Gas turbine combustion apparatus. USP2007117299618.
  13. Cornelius Walter (Troy MI) Klomp Edward D. (Mt. Clemens MI). Gas turbine combustor assembly. USP1984014426841.
  14. Mongia Hukam C. (Tempe AZ) Coleman Edwin B. (Tempe AZ) Bruce Thomas W. (Phoenix AZ). Gas turbine combustor operating method. USP1986064594848.
  15. Bland, Robert J.. Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions. USP2011017870739.
  16. Mowill, R. Jan. Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities. USP2005086925809.
  17. Mongia Hukam C. (Tempe AZ) Coleman Edwin B. (Tempe AZ) Bruce Thomas W. (Pheonix AZ). Gas turbine engine variable geometry combustor apparatus. USP1985084532762.
  18. Elliott, Gerald R.; Linderoth, Carl E.; McConnell, Clifford T.; Short, Alvin D.. Integrated biomass energy system. USP2012088240123.
  19. Hellat, Jaan; Riccius, Oliver; Smith, Richard; Viereck, Detlef. Method for operating a gas turbine. USP2009047516608.
  20. Belsom, Keith Cletus. Methods and apparatus for assembling gas turbine engines. USP2009127631504.
  21. Myers, Geoffrey David; Davis, Jr., Lewis Berkley; Healy, Timothy Andrew; Citeno, Jospeh. Methods and systems for controlling a combustor in turbine engines. USP2012018099941.
  22. Mowill R. Jan,NLX. Premixer with dilution air bypass valve assembly. USP1999075924276.
  23. Yamaguchi Shigeki (Nagoya JPX) Ohiwa Norio (Nagoya JPX) Ishiguro Katsusuke (Nagoya JPX). Pulse combustion device. USP1989114881373.
  24. Hudson Dale A. (Beavercreek OH) Hopkins Kenneth N. (Centerville OH). Sector airflow variable geometry combustor. USP1988014720970.
  25. Mowill R. Jan (OPRA B.V. Opaalstraat 60 ; P.O. Box 838 7550 AV Hengelo NLX). Star combustor with dilution ports in can portions. USP1997055628182.
  26. McEvoy, Lawrence J.; Jacobsen, Eric; Jacobsen, Krista; Jacobsen, John G.. Superatmospheric combustor for combusting lean concentrations of a burnable gas. USP2004116814568.
  27. Goodwin, Martin S.. Swirler for a fuel injector. USP2013088511091.
  28. Antoniono, Carolyn Ashley; Byrne, William Lawrence; Fadde, Elizabeth Angelyn. System and method for a turbine combustor. USP2017049631815.
  29. Stoia, Lucas John; Romig, Bryan Wesley; Johnson, Thomas Edward; Stevenson, Christian Xavier. System and method for supplying a working fluid to a combustor. USP2015069052115.
  30. Umeh, Chukwueloka Obiora; Haynes, Joel Meier; Goldmeer, Jeffrey Scott. System for controlling combustion dynamics and method for operating the same. USP2014128915086.
  31. Stoia, Lucas John; Melton, Patrick Benedict; Popovic, Predrag Peja. Turbine engine and method for flowing air in a turbine engine. USP2015049010082.
  32. Sanders,Noel A; Bourne,Carl C; Moran,Anthony J; Fletcher,Paul; Walsh,Philip P. Variable geometry combustor. USP2009037500347.
  33. Sampath Parthasarathy,CAX ; Davenport Nigel Caldwell,CAX. Variable premix-lean burn combustor. USP2001076253538.