$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Low-nox, rich-lean combustor

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02E-001/00   
미국특허분류(USC) 60/723 ; 60/732 ; 60/753
출원번호 US-0621129 (1984-06-15)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 28  인용 특허 : 8
초록

A low-NOx combustor is provided with a rich, primary burn zone and a lean, secondary burn zone. NOx formation is inhibited in the rich burn zone by an oxygen deficiency and in the lean burn zone by a low combustion reaction temperature.

대표
청구항

A low-NOx combustor for heating compressor discharge gases to drive a turbine, comprising: a basket having a wall for containing combustion therein and further having an upstream zone for fuel rich, diffusion flame combustion and a downstream zone for fuel-lean combustion with a necked-down quench zone connecting said cumbustion zones; means for injecting fuel into the upstream end of said basket; means for enabling fuel-rich combustion of the fuel injected by said injecting means in said fuel-rich combustion zone; means for introducing a quench air flow...

이 특허를 인용한 특허 피인용횟수: 28

  1. Teets, J. Michael. Annular combustor for use with an energy system. USP2005016845621.
  2. Burd, Steven W.; Sowa, William; Cheung, Albert K.; Kramer, Stephen Karl; Smith, Reid Dyer Curtis; Hoke, James. Annular gas turbine combustor including converging and diverging segments. USP2014038671692.
  3. Hoke, James B.. Axial stage combustor for gas turbine engines. USP2015069068748.
  4. Craig Joe D. (P.O. Box 70 Tahoka TX 79373). Biomass gasification system and method. USP1997095666890.
  5. Hums Erich,DEX ; Vortmeyer Nicolas,DEX. Catalytic combustion chamber operating on preformed fuel, preferably for a gas turbine. USP1999095946917.
  6. Willis Jeffrey W. (Los Angeles CA) Belmont James E. (Canoga Park CA). Catalytic combustion system. USP1997115685156.
  7. Coffinberry George A.. Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits. USP1999045891584.
  8. Coffinberry George A. ; Ackerman John F.. Coated articles and method for the prevention of fuel thermal degradation deposits. USP1998095805973.
  9. Wilkes Colin (Lebanon IN) Mongia Hukam C. (Carmel IN) Tramm Peter C. (Indianapolis IN). Combustion system. USP1990094958488.
  10. Boardman, Gregory Allen; Naik, Pradeep; Danis, Allen Michael. Combustor assembly for a turbine engine. USP20190210197279.
  11. Dai, Zhongtao; Cohen, Jeffrey M.; Kopp-Vaughan, Kristin; Hoke, James B.. Combustor assembly for a turbine engine. USP2018059958162.
  12. Rudrapatna, Nagaraja S.; Frye, Lowell; Landram, William. Combustors with quench inserts. USP2015069062884.
  13. Williams, Arthur R.; Agosta, Charles. Cylindrical Bernoulli heat pumps. USP2013038402784.
  14. Nalim, Razi; Akbari, Pejman. Direct injection of a discrete quantity of fuel into channels of a wave rotor engine. USP2014118893467.
  15. Burd,Steven W.; Cheung,Albert K.; Ols,John T.; Smith,Reid D.; Segalman,Irving. Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume. USP2006087093441.
  16. Hoke, James B.. Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies. USP2013078479521.
  17. Willis, Jeffrey W.; Pont, Guillermo; Toby, Benjamin E.; McKeirnan, Jr., Robert D.. Gas turbine engine having a multi-stage multi-plane combustion system. USP2004026684642.
  18. Grote, Holger; Kollenberg, Wolfgang; Tertilt, Marc. Heat shield element, in particular for lining a combustion chamber wall. USP2014108857190.
  19. Simons,Derrick Walter; Amond, III,Thomas Charles; Gupta,Ajay Kumar. Inboard radial dump venturi for combustion chamber of a gas turbine. USP2008067389643.
  20. Hoke James B. ; Segalman Irving ; Siskind Kenneth S. ; Smith Reid D. C.. Low NOx combustor for gas turbine engine. USP2001066240731.
  21. Plichta Peter,DEX. Method and apparatus for operating a gas turbine with silane oil as fuel. USP1999125996332.
  22. Jeffery W. Willis ; Guillermo Pont ; Benjamin E. Toby ; Robert D. McKeirnan, Jr.. Multi-stage multi-plane combustion system for a gas turbine engine. USP2002096453658.
  23. Teets, Joseph Michael. Radially staged RQL combustor with tangential fuel-air premixers. USP2014048701416.
  24. Prociw, Lev Alexander; Kojovic, Aleksander; Jamon, David C.; Shi, Jun; Butler, Shaoluo L.. Reverse flow ceramic matrix composite combustor. USP2016089423130.
  25. Prociw, Lev Alexander; Kojovic, Aleksander; Jarmon, David C.; Shi, Jun; Butler, Shaoluo L.. Reverse flow ceramic matrix composite combustor. USP2014068745989.
  26. Kraemer, Gilbert Otto. Rich burn, quick mix, lean burn combustor. USP2016049310082.
  27. Slobodyanskiy, Ilya Aleksandrovich; Davis, Jr., Lewis Berkley; Minto, Karl Dean. System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation. USP2018029903588.
  28. Robertson ; Jr. Arichbald Stuart ; Lu Chongqing ; Fan Zhen. Topping combustor for low oxygen vitiated air streams. USP1999095950417.