全环涡轮级间燃烧室性能试验

宋双文; 胡好生; 王梅娟; 陈剑; 王录峰

全环涡轮级间燃烧室性能试验

中国航空工业集团公司航空动力机械研究所,湖南株洲 412002

计量
- 文章访问数: 1956
- HTML浏览量: 112
- PDF量: 610
- 被引次数: 0
出版历程
- 收稿日期: 2012-05-18
- 刊出日期: 2012-10-28

Experiment on performance of annular interstage turbine burner

Aviation Powerplant Research Institute,Aviation Industry Corporation of China, Zhuzhou Hunan 412002,China

摘要

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.
- 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
Abstract: 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.
- trapped vortex combustor /
- interstage turbine burner(ITB) /
- ignition performance /
- combustor performance /
- liner wall temperature

HTML

参考文献(15)

[1]	Sirignano W A,Delplanque J P,Liu F,et al.Selected challenges in jet and rocket engine combustion research .AIAA 97-2701,1997.
[2]	Siow Y K,Yang S L.Numerical study and design of interstage turbine burner .AIAA 2002-3727,2002.
[3]	Thornburg H,Sekar B,Zelina J,et al.Numerical study of an inter-turbine burner (ITB) concept with curved radial vane .AIAA 2007-649,2007.
[4]	Mawid M A,Thornburg H,Sekar B,et al.Performance of an inter-turbine burner (ITB) concept with three-different vane cavity shapes .AIAA-2006-4740,2006.
[5]	Roquemore W M,Shouse D,Burrus D,et al.Vortex combustor concept for gas turbine engines .AIAA 2001-0483,2001.
[6]	Zelina J,Ehret J,Hancock R D,et al.Ultra-compact combustion technology using high swirl for enhanced burning rate .AIAA-2002-3725,2002.
[7]	孔昭健,樊未军,易琪,等.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. KONG Zhaojian,FAN Weijun,YI Qi,et al.Ignition and lean blow out performance of trapped vortex combustor with evaporating tubes fuel injection[J].Journal of Aerospace Power,2007,22(7):1132-1137.(in Chinese)
[8]	邢菲,张荣春,樊未军,等.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. XING Fei,ZHANG Rongchun,FAN Weijun,et al.Experimental study on single/fuel-lean trapped vortex combustor ignition and limit blow-out at different main air and mix air temperatures[J].Journal of Aerospace Power,2008,23(12):2280-2285.(in Chinese)
[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. HE Xiaomin,YAO Feng.Effect of flow parameters and equivalence ratio on the trapped vortex combustor performance[J].Journal of Aerospace Power,2006,21(5):810-813.(in Chinese)
[10]	Liu F,Sirignano W A.Turbojet and turbofan engine performance increases through turbine burners .AIAA 2000-0741,2000.
[11]	Liew K H,Urip E,Yang S L,et al.Complete parametric cycle analysis of a turbofan with interstage turbine burner .AIAA 2003-0685,2003.
[12]	Liew K H,Urip E,Yang S L,et al.Performance cycle analysis of a two-spool,separate-exhaust turbofan with interstage turbine burner .AIAA 2004-3311,2004.
[13]	潘旭,葛宁.带涡轮燃烧室的涡扇发动机设计点性能分析[J].燃气涡轮试验与研究,2007,20(3):34-38. PAN Xu,GE Ning.Parametric(on-design) analysis for a separate-exhaust turbofan engine with interstage turbine burner[J].Gas Turbine Experiment and Research,2007,20(3):34-38.(in Chinese)
[14]	Liu F,Sirignano W A.Turbojet and turbofan engine performance increase through turbine burners[J].Journal of Propulsion and Power,2001,17(3):695-705.
[15]	Chen G,Hoffman M A,Davis R L.Improvements in gas-turbine performance through the use of multiple turbine inter-stage burners .AIAA 2004-374,2004.