全环涡轮级间燃烧室性能试验  

Experiment on performance of annular interstage turbine burner

作　　者：宋双文[1] 胡好生[1] 王梅娟[1] 陈剑[1] 王录峰[1] 

机构地区：[1]中国航空工业集团公司航空动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2012年第10期2175-2179,共5页Journal of Aerospace Power

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.

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 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]