期刊文献+

全环涡轮级间燃烧室性能试验 被引量:4

Experiment on performance of annular interstage turbine burner
原文传递
导出
摘要 以涡轮级间燃烧室(ITB)应用于涡轴发动机为研究平台,根据ITB的应用环境,采用凹腔驻涡燃烧室作为涡轮级间燃烧室,设计加工了全环凹腔驻涡燃烧室试验件,并进行了性能试验研究.试验结果表明:该燃烧室的贫油点火边界余气系数为10.2,降低驻涡凹腔体内外压差有利于点火;与常规燃烧室相比,燃烧室的燃烧效率偏低,但燃烧效率随进口温度的升高逐步加大;燃烧室的总压恢复系数较小,进口温度对燃烧室的总压恢复系数影响不大;燃烧室出口温度场分布较好,出口温度分布系数(OTDF)随进口温度的升高而减小;随着进口温度的提高,火焰筒壁温会局部偏高,火焰筒的冷却设计需优化改进. According to the interstage turbine burner(ITB)operation condition,an ITB annular combustor test rig,which used trap vertex combustor design,was designed and manufactured based on ITB being used in a certain turbo-shaft engine,and combustor performance experiment study was performed.The results show that: the lower flammable limit of the ITB is 10.2,and it is favorable to ignite when the pressure difference between the inner of the cavity and the outer of the cavity is reduced.As compared with the ordinary combustor,the combustion efficiency of the ITB is lower,and the combustion efficiency improves when the inlet temperature increases.The total pressure recovery coefficient of the ITB is lower,and the variation of inlet temperature has a less effect on the pressure recovery coefficient.The outlet temperature distribution factor(OTDF) is good,and the outlet temperature distribution factor decreases when the inlet temperature increases.When the inlet temperature increases,the wall temperature of the liner would be partially higher,and the cooling design of the liner should be optimized.
出处 《航空动力学报》 EI CAS CSCD 北大核心 2012年第10期2175-2179,共5页 Journal of Aerospace Power
关键词 驻涡燃烧室 涡轮级间燃烧室(ITB) 点火性能 燃烧室性能 火焰筒壁温 trapped vortex combustor interstage turbine burner(ITB) ignition performance combustor performance liner wall temperature
  • 相关文献

参考文献15

  • 1Sirignano W A, Delplanque J P, I.iu F, et al. Selected challenges in jet and rocket engine combustion research[R]. AIAA 97-2701,1997.
  • 2Slow Y K, Yang S L. Numerical study and design of interstage turbine burner[R]. AIAA 2002 3727,2002.
  • 3Thornburg H, Sekar B, Zelina J, et al. Numerical study of an inter-turbine burner (ITB) concept with curved radial vane[R]. AIAA 2007-649,2007.
  • 4Mawid M A,Thornburg H, Sekar B, et al. Performance of an inter-turbine burner (ITB) concept with three-different vane cavity shapes[R]. AIAA-2006-4740,2006.
  • 5Roquemore W M,Shouse D,Burrus D, et al. Vortex combustor concept for gas turbine engines[R]. AIAA 2001- 0483,2001.
  • 6Zelina J, Ehret J, Hancock R D, et al. Ultra compact combustion technology using high swirl for enhanced burning rate[R]. AIAA-2002-3725,2002.
  • 7孔昭健,樊未军,易琪,刘玉英,杨茂林.采用蒸发管供油的驻涡燃烧室点火及贫油熄火特性[J].航空动力学报,2007,22(7):1132-1137. 被引量:12
  • 8邢菲,张荣春,樊未军,柳杨,闫永强.主流及掺混气温度对单涡/贫油驻涡燃烧室点火及熄火性能影响的试验[J].航空动力学报,2008,23(12):2280-2285. 被引量:11
  • 9何小民,姚锋.流动和油气参数对驻涡燃烧室燃烧性能的影响[J].航空动力学报,2006,21(5):810-813. 被引量:20
  • 10Liu F, Sirignano W A. Turbojet and turbofan engine per formance increases through turbine burners [R]. AIAA 2000-0741,2000.

二级参考文献26

  • 1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
  • 2樊未军,易琪,严明,杨茂林.驻涡燃烧室凹腔双涡结构研究[J].中国电机工程学报,2006,26(9):66-70. 被引量:47
  • 3Bahr D W. Technology for the design of high temperature rise combustors[R]. AIAA-85-1292.
  • 4Hsu K Y, Goss L P, Trump D. Performance of a trappedvortex combustor[R]. AIAA95-0810.
  • 5Hsu K Y, Goss L P. Characteristics of a trapped-vortex combustor[J]. Journal of Propulsion and Power, 1998, 14(1) :57-65.
  • 6Burrus D L, Johnson A W, Roquemore W M, et al. Per formanee assessment of prototype trapped vortex comhus tor concept for gas turbine application[R]. ASME 2001 GT-0087.
  • 7Roquemore W M, Shouse D, Dave B, et al. Trapped vortex combustor concept for gas turbine engines[R]. AIAA 2001-0483.
  • 8Meyer T R, Brown M S, Fonov S, et al. Optical diagnostics and numerical characterization of a trapped-vortex comhustor [R]. AIAA 2002-3863.
  • 9Hendricks R C, Shouse D T, Roquemore W M. Water in jected turbomachinery[R]. NASA/TM-2005-212632.
  • 10廉小纯,吴虎.航空燃气轮机原理[M].北京:国防工业出版社,2001.

共引文献40

同被引文献38

  • 1李名家,钱程,何万国,林枫.燃气轮机燃烧室故障分析及试验研究[J].热能动力工程,2010,25(5):478-481. 被引量:10
  • 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樊未军,易琪,严明,杨茂林.驻涡燃烧室凹腔双涡结构研究[J].中国电机工程学报,2006,26(9):66-70. 被引量:47
  • 4耿小亮,郭运强,张克实,秦亮.火焰筒热疲劳分析与寿命估计[J].机械强度,2007,29(2):305-309. 被引量:9
  • 5Hsu K Y, Goss L P, Trump D D, et al. Performance of a Trapped-Vortex Combustor[ R ]. AIAA 95-0810.
  • 6Hsu K Y, Gross L P. Characteristics of a Trapped Vor- tex Combustor [J]. Journal of Propulsion and Power, 1998, 14(1):57 -65.
  • 7Meyer T R, Brown M S, Fonov S, et, al. Optical Diag- nostics and Numerical Characterization of a Trapped- Vortex Combustor[ R ]. AIAA 2002-3863.
  • 8Burrus D L, Johnson A W, Roquemore W M, et al. Per- formance Assessment of a Prototype Trapped Vortex Combustor Concept for Gas Turbine Application [R]. ASME 200 I-GT-0087.
  • 9Roquemore W M, Dale Shouse, Dave Burrus, e|, al. Trapped Vortex Combustor Concept for Gas Turbine En- gines[ R ]. AIAA 2001-0483.
  • 10Krlshna Kant Agarwal, R V Ravikrishna. Experimental and Numerical Studies in a Compact Trapped Vortex Combustor: Stability Assessment and Augmentation [J]. Combustion Science and Technology, 2011, 183 (12): 1308-1327.

引证文献4

二级引证文献17

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