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특허 상세정보

MyON담기
내보내기 페이스북 공유 카카오톡 공유

Combustor for a low-emissions gas turbine engine

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02G-003/00    F02C-007/20   
미국특허분류(USC) 600/390.2 ; 600/393.2 ; 607/52
출원번호 US-0093375 (1998-06-08)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Roberson
인용정보 피인용 횟수 : 42  인용 특허 : 5
초록
▼

Many government entities regulated emission from gas turbine engines including CO. CO production is generally reduced when CO reacts with excess oxygen at elevated temperatures to form CO2. Many manufactures use film cooling of a combustor liner adjacent to a combustion zone to increase durability of the combustion liner. Film cooling quenches reactions of CO with excess oxygen to form CO2. Cooling the combustor liner on a cold side (backside) away from the combustion zone reduces quenching. Furthermore, placing a plurality of concavities on the cold sid...

대표
청구항
▼

[ We claim:] [22.] A method for reducing emissions of a gas turbine engine comprising the steps of:directing a volume of air having a first pressure to a combustor, said combustor having a combustor cooling shield, a combustor liner, and a cooling channel between said combustor cooling shield and said combustor liner, said combustor liner having an inlet portion, an outlet portion, and a plurality of concavities adjacent said combustor cooling shield, said concavities being adapted to retard growth of a thermal boundary layer;diverting a first portion of...

이 특허에 인용된 특허 (5)

  1. Alkabie Hisham Salman,GBX. Combuster and operating method for gas-or liquid-fuelled turbine arrangement. USP1998075784876.
  2. Loprinzo Anthony J. (Clifton Park NY). Dilution flow sleeve for reducing emissions in a gas turbine combustor. USP1996115575154.
  3. Dillard Gary J. (Stuart FL) McAlice Timothy J. (Jupiter FL). Gas turbine exhaust liner with milled air chambers. USP1997015596870.
  4. Abreu Mario E. ; Sood Virenda M.. Impingement/effusion cooled combustor liner. USP1998065758504.
  5. Shaffer James E. (Maitland FL) Holsapple Allan C. (Poway CA). Wedge edge ceramic combustor tile. USP1997065636508.

이 특허를 인용한 특허 피인용횟수: 42

  1. Bunker, Ronald Scott; Wei, Bin; Hasz, Wayne C.; Massimiliano, Nania. Air cooled heat exchanger with enhanced heat transfer coefficient fins. USP2010067743821.
  2. Chen, Wei; Fulcher, Stephen. Angled vanes in combustor flow sleeve. USP2013088516822.
  3. Kwon, Okey. Augmented cooling system. USP2017059638057.
  4. Lipinski, John Joseph; Johnson, Thomas Edward; Ziegler, Robert Paul; Schroder, Mark Stewart. Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air. USP2010057707835.
  5. Lutjen, Paul M.; Strock, Christopher W.. Ceramic coating systems and methods. USP2013098535783.
  6. Kesseli, James B.; Nash, James S.. Ceramic-to-metal turbine shaft attachment. USP2015069051873.
  7. Baldwin, Matthew Stephen. Ceramic-to-metal turbine volute attachment for a gas turbine engine. USP20181010094288.
  8. Tiemann, Peter. Collar for a combustion chamber of a gas turbine engine. USP2005116968672.
  9. Froehlich, Anton. Combustion chamber comprising a cooling unit and method for producing said combustion chamber. USP2009107603843.
  10. Froehlich, Anton. Combustion chamber comprising a cooling unit and method for producing said combustion chamber. USP2013108567061.
  11. Green,Andrew; Stuttaford,Peter; Carella,John; Duraibabu,Vamsi; Jennings,Stephen. Combustion liner with enhanced heat transfer. USP2008067386980.
  12. Cihlar, David William; Chila, Ronald James; Berkman, Mert Enis. Combustor assemblies for use in turbine engines and methods of assembling same. USP2014088813501.
  13. Bunker,Ronald Scott; Bailey,Jeremy Clyde; Widener,Stanley Kevin; Johnson,Thomas Edward. Combustor cooling with angled segmented surfaces. USP2008057373778.
  14. Roldan-Posada, Carlos. Combustor liner assembly with enhanced cooling system. USP2014038667801.
  15. Chila, Ronald James. Combustor liner cooling system. USP2012118307657.
  16. Bunker,Ronald Scott. Combustor liner with inverted turbulators. USP2006097104067.
  17. Bunker, Ronald Scott. Combustor liner with ring turbulators and related method. USP2004016681578.
  18. Vetters, Daniel K.. Combustor with tiled liner. USP2017049612017.
  19. Bunker, Ronald Scott; Wei, Bin. Cooling passages and methods of fabrication. USP2003116644921.
  20. Benz,Urs; Hellat,Jaan; Joos,Franz. Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system. USP2006097104065.
  21. Bunker, Ronald Scott. Double wall combustor liner segment with enhanced cooling. USP2004076761031.
  22. Moraes, Ricardo F.. Elimination of plate fins in combustion baskets by CMC insulation installed by shrink fit. USP2014018627669.
  23. Bryk,Roderich; Gossmann,Otmar; H철ll,Harald; Voss,Burkhard. Gas turbine and method for damping oscillations of an annular combustion chamber. USP2006016988366.
  24. Ikeda,Kazufumi; Ishiguro,Tatsuo; Tanaka,Katsunori; Tanimura,Satoshi. Gas turbine combustor. USP2006087089741.
  25. Markarian, Lorin; Patel, Bhawan B.. Gas turbine floating collar arrangement. USP2010047690207.
  26. Nirmalan, Nirm Velumylm; Bowman, Michael John. Heat exchanger for power generation equipment. USP2005066904747.
  27. Bunker,Ronald Scott; Bailey,Jeremy Clyde; Lee,Ching Pang. Hot gas path component with mesh and dimpled cooling. USP2007037186084.
  28. Bunker,Ronald Scott; Lee,Ching Pang. Hot gas path component with mesh and impingement cooling. USP2007027182576.
  29. Bunker,Ronald Scott; Bailey,Jeremy Clyde; Lee,Ching Pang. Hot gas path component with mesh and turbulated cooling. USP2006016984102.
  30. Beck, Christian; Bez, Simon; Buchholz, Bjorn; Grieb, Thomas; Hase, Matthias; Krebs, Werner; Kostlin, Berthold; Reich, Stefan; Tertilt, Marc; Wilkes, Jan. Jet burner with cooling duct in the base plate. USP20181010088163.
  31. Bunker, Ronald Scott. Linear surface concavity enhancement. USP2004046722134.
  32. Hessler, William K.; Popovic, Predrag; Nyberg, Charles. Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface. USP2012018096133.
  33. Bunker,Ronald Scott; Bailey,Jeremy Clyde; Widener,Stanley Kevin; Johnson,Thomas Edward; Intile,John C. Method and apparatus for cooling combustor liner and transition piece of a gas turbine. USP2009027493767.
  34. Intile,John Charles; West,James A.; Byrne,William. Method and apparatus for cooling combustor liner and transition piece of a gas turbine. USP2006037010921.
  35. Huffman, Marcus B.. Method and apparatus to enhance transition duct cooling in a gas turbine engine. USP2013108549861.
  36. McMahan, Kevin Weston; Chila, Ronald James; Johns, David Richard. Methods and systems for cooling a transition nozzle. USP2015038966910.
  37. Widener,Stanley Kevin; McMahan,Kevin Weston; Johnson,Thomas Edward. One-piece can combustor. USP2006087082766.
  38. Rubio, Mark B.; Ritland, David M.. Segmented annular combustor. USP2011017874138.
  39. Pinard, Pierre Francois; Tangirala, Venkat Eswarlu; Rasheed, Adam; Dean, Anthony John; Bunker, Ronald Scott; Chapin, David Michael. Shaped walls for enhancement of deflagration-to-detonation transition. USP2010037669405.
  40. Liang, George. Transition duct with spiral finned cooling passage. USP2012118307654.
  41. Hasz, Wayne Charles; Abuaf, Nesim; Johnson, Robert Alan; Lee, Ching-Pang. Turbine engine component having enhanced heat transfer characteristics and method for forming same. USP2003076589600.
  42. Johnson, Thomas Edward; Melton, Patrick. Turbulated aft-end liner assembly and cooling method. USP2013108544277.

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