不同叶片径向凹槽结构的超紧凑型涡轮级间燃烧室数值模拟  

Numerical Investigation of Interstage-Turbine Burner(ITB) with Different Radial Vane Cavity Shapes

作　　者：骆广琦[1] 孟龙[1] 刘琨[1] 

机构地区：[1]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2012年第3期6-10,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：空军工程大学学术创新基金资助项目(XS1011004)

摘　　要：利用流体计算软件,采用Realizable k-ε湍流模型和PDF输运燃烧模型,分别对无凹槽和5种不同径向凹槽叶片结构的超紧凑型涡轮级间燃烧室(ITB)三维两相燃烧流场进行了数值模拟,并比较分析了不同ITB模型的速度场、温度场和总体性能参数。计算结果表明不同叶片径向凹槽结构内部的速度场、温度场差异较大,进而影响到富油燃烧产物在主流下游通道进行二次贫油燃烧的完全程度和ITB出口截面温度分布。改进叶片径向凹槽结构可以使级间燃烧室总压损失更小、燃烧效率和温升更高、出口污染物浓度更低。Inter - stage - turbine burner（ ITB ） with no radial vane cavity and five different kinds of radial vane cav- ity shapes three - dimensional combustor model on two phase combustion flows are simulated by utilizing a computa- tional fluid dynamics software together with k - e model and simplified PDF combustion model. Velocity field, tem- perature field and overall performance of different kinds of ITB models are compared and analyzed. The result shows that the different radial vane cavity shapes differ on the velocity and temperature field in the radial vane cavity, and then have an influence on the combustion completeness of the rich burn products and outlet temperature. By chan- ging the radial vane cavity shapes, ITB can obtain higher combustion effeciency and outlet temperature, smaller pressure drop and better species concentration standard.

关 键 词：涡轮级间燃烧室 径向凹槽 高温区 组分浓度 

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]