燃烧环长宽比对涡轮叶间燃烧室的影响  

Influence of Length-Width Ratio of Combustion Ring on Turbine Inter-Vane Burner

作　　者：徐兴亚[1] 唐豪[1] 郑海飞[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2014年第2期6-9,5,共5页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(51076064)

摘　　要：为研究燃烧环结构对涡轮叶间燃烧室的性能影响,通过改变燃烧环的径向长度,设计出6种不同长宽比的燃烧环模型,并利用FLUENT软件的Realizable k-ε湍流模型、PDF燃烧模型和离散相模型,对涡轮叶间燃烧室三维两相流场进行了数值模拟。结果表明:受高温燃气与主流掺混程度的影响,不同长宽比燃烧环内速度场及温度场差异明显,从而影响燃油液滴驻留时间和出口温度分布;合理选择燃烧环的长宽比,能有效改善涡轮叶间燃烧室的燃烧效率、总压损失和温度分布。本研究可为涡轮叶间燃烧室优化设计提供参考。To study the influence of combustion ring structure on Turbine Inter-Vane Burner （TIB）, six kinds of combustion ring with different length-width ratio were designed by changing radial length of com-bustion ring. The realizable k-εturbulent model, PDF combustion model and DPM model of FLUENT were used to simulate the three-dimensional and two phase combustion in the burner. The results show that the degree of mixing of the high temperature gas and the main flow affect the velocity field and temperature field in combustion ring with different length-width ratio, thereby changing the combustion completeness and the distribution of outlet temperature. Choosing the length-width ratio of combustion ring reasonably can improve the combustion efficiency, total pressure loss and the distribution of temperature of TIB. The re-sults of numerical simulation can be referential for designing TIB.

关 键 词：涡轮叶间燃烧室 超紧凑燃烧室 燃烧环 长宽比 温度分布 数值模拟 turbine inter-vane burner(TIB) 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]