期刊文献+

RQL燃烧室污染物排放的数值研究 被引量:2

Numerical study of pollutants emission characteristics in RQL combustion chamber
下载PDF
导出
摘要 针对RQL模型燃烧室中不同的操作条件对污染物排放特性的的影响进行了数值模拟。当量比从1到1.2,富油区不能有效抑制出口NOX的生成;当量比1.5以上会使贫油区油气比过高从而使NOX浓度升高。对于给定当量比1.4时,当适当增大淬熄射流流量能够有效的降低NOX、Soot、CO的出口浓度;过多的增加,NOX、Soot、CO的出口浓度会再次升高。 The numerical simulation for the effect of flow distribution on the characteristics of pollutant emission is investigated under different operating conditions in this paper.It is found that,for a given flow distribution,the NOx emission can not be prevented effectively with the equivalence ratio varying from 1 to 1.2 in fuel rich zone;NOx emission increases as a result of the extra fuel-air mass ratio in fuel lean zone when the equivalence ratio is above 1.5.For a given equivalence ratio of 1.4,when the quench flow rate increases appropriately,the emission concentration of NOx,Soot and CO can be effectively reduced;conversely,when the quench flow rate increases excessively the emission concentration of NOx,Soot and CO increases.
出处 《沈阳航空航天大学学报》 2011年第2期16-20,共5页 Journal of Shenyang Aerospace University
关键词 RQL燃烧室 数值模拟 当量比 流量分配 污染物排放 RQL combustor numerical simulation equivalence ratio flow rate distribution pollutant emission
  • 相关文献

参考文献6

  • 1A.S.Feitelberg.The GE Rich-Quench-Lean gad turbine com-bustor. Jornal of Engineering for Gas Turbines and Power . 1998 被引量:1
  • 2A.Vranos,,D.S.Liscinsky.Experimental study ofcross-stream mixing in a cylindrical duct. NASA TM-105180,AIAA-91-2459 . 1991 被引量:1
  • 3James D.Holdeman.The effects of air preheat andnumber of orifices on flow and emissions in an rqlmixing section. National Aeronautics a Space Ad-ministration . 2007 被引量:1
  • 4P.Weigand,,W.Merier.Inwestigations of swirl flamesin a gas turbine model combustor. Combustion and Flame . 2005 被引量:1
  • 5C.Hassa,,C.E.Migueis,,P.Voigt.Design principles forthe quench zone of Rich-Quench-Lean combustor. RTO AVT Symposium . 1998 被引量:1
  • 6赵坚行.民用发动机污染排放及低污染燃烧技术发展趋势[J].航空动力学报,2008,23(6):986-996. 被引量:86

二级参考文献15

  • 1Bahr W W, Gleason C C. Experiment clean combustor program, Phase I: Final reportERS. NACA-CR-134737, 1975. 被引量:1
  • 2Lew L H, Carl D R, Dezubay E A. Low NOx heavy fuel combustor concept program Phase I: Combustion technology generation[R]. NASA-CR-165482, 1981. 被引量:1
  • 3Mongia H C. TAPS-A4^th generation propulsion comhustor technology for low emissions [R]. AIAA 2003-2657, 2003. 被引量:1
  • 4Marek C J, Smith T D. Low emission hydrogen combustots for gas turbines using lean direct injection[R]. AIAA 2005 3776,2005. 被引量:1
  • 5Walker A D, Denman P A, McGuirk J J. Experimental and computational study of hybrid diffusers for gas turbine combustors[J]. ASME J. of Engineering Gas Tur hines and Power,2004, 126:717 725. 被引量:1
  • 6Rizk N K, Chin J S. Modeling of NOx formation in diffusion flame combustors[R]. AIAA 2002 3713, 2002. 被引量:1
  • 7Smith L L, Karim H, Castaldi M J. Rich-catalytic leanburn combustion for low-singht-digit NOx gas turbines[J]. ASME J. of Engineering for Gas Turbines and Pow er, 2005, 127: 27. 被引量:1
  • 8Rizk N K, Mongia H C. Three dimensional emission modeling for diffusion flame, rich/lean and lean gas turbine combustors[R]. AIAA 93-2338,1993. 被引量:1
  • 9Imamura A ,Yoshida M. Research and development of a LPP combustor with swirling flow for low NOx [R]. AIAA 2001 3311, 2001. 被引量:1
  • 10Douglas L, Straub K H. Assessment of rich burn, quick mix, lean-burn trapped vortex combustor for stationary gas turbines[J]. ASME J. of Engineering for GasTurhines and Power, 2005, 127: 36-41. 被引量:1

共引文献85

同被引文献21

  • 1王平,张宝诚.航空发动机燃烧室主燃区的数值模拟分析[J].航空发动机,2005,31(1):47-51. 被引量:6
  • 2樊未军,严明,易琪,杨茂林.富油/快速淬熄/贫油驻涡燃烧室低NO_x排放[J].推进技术,2006,27(1):88-91. 被引量:31
  • 3林宇震,刘高恩,许全宏.未来航空燃气轮机燃烧室关键技术探讨[c]//第五届动力年会论文集.北京:中国航空学会,2003:5-8. 被引量:1
  • 4Roquemore W M, Shouse D, Burrus D, et al. Trapped Vortex Combus- tor concept for gas turbine engines [R]. AIAA-2001-0483. 被引量:1
  • 5Straub D L, Casleton K H, Lewis R E, et al. Assessment of Rich-bum, Quick-mix,Lean-burn Trapped Vortex Combustor for stationary- gas turbines [J]. Journal of Engineering for Gas Turbines and Power, 2005,127:36-41. 被引量:1
  • 6《航空发动机设计手册》总编委会.航空发动机设计手册:第9册主燃烧室[M].北京:航空工业出版社,2001:37-40,410-433. 被引量:1
  • 7Hsu K Y,Goss L P,Roquemore W M. Characteristics of a Trapped-Vortex Combustor [J]. Journal of Propulsion and Power, 1998,14( 1 ) : 57-65. 被引量:1
  • 8Hsu K Y,Goss L P,Trump D D. Performance of a Trapped-Vortex Combustor [R]. AIAA-95-0810. 被引量:1
  • 9Komerath N M, Ahuja K K, Chambers F W. Prediction and measurement of flows over cavities -a survey [R].AIAA-87-0166. 被引量:1
  • 10Straub D L,Sidwell T G, Maloney D J, et al. Simulations of a Rich Quench Lean (RQL) trapped vortex combustor [C]//The American Flame Research Committee International Symposium Newport Beach, USA:CA,2000:1-11. 被引量:1

引证文献2

二级引证文献2

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部