径向槽对涡轮叶间补燃室性能影响的数值研究  

Numerical investigation of influence of radial vane cavity on turbine inter-vane burner performance

作　　者：李明[1,2] 唐豪[1] 郑海飞[1] 李炎[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]中国航空工业集团公司中航空天发动机研究院有限公司,北京100028

出　　处：《航空动力学报》2014年第12期2836-2844,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51076064)

摘　　要：为探究径向槽对涡轮叶间补燃室的影响,设计了两种涡轮叶间补燃室模型.用计算流体动力学的方法对涡轮叶间补燃室内流动及燃烧进行数值模拟,数值模拟结果与实验数据基本吻合.涡轮叶间补燃室性能稳定,燃烧效率在97.5%以上,绝对压力损失为5.7%.叶背径向槽会引起气流在叶背发生分离,流场遭严重破坏,叶盆径向槽会减弱分离现象,改善出口径向平均速度分布.叶盆径向槽可提高燃烧效率,降低叶片表面温度,使叶间、出口温度更均匀.叶盆径向槽较叶背径向槽能降低CO、未燃碳氢化合物的排放量,但会引起NO排放量增加.Two turbine inter-vane burner（TIB）models with different radial vane cavities（RVC）were designed to investigate the influence of RVC on TIB.Computational fluid dynamic method was carried out to simulate the turbulent flow and combustion in the TIB.Comparisons show that the simulation results accord well with the experimental data.TIB performs well with 97.5% or higher combustion efficiency and 5.7% pressure loss.Airflow is detached from the convex surface of the vane with RVC in the same surface and the flow field is changed drastically.The RVC in the concave surface can alleviate the detachment and mitigate the radial profile of velocity distribution at the outlet.In the TIB with RVC in the concave surface of the vane,the combustion efficiency is relatively higher;the vane temperature is lower and the temperature distribution is more uniform in the passage and outlet.The emission of CO and unburned hydrocarbon is lower in the TIB with RVC in the concave sur-face.However,the emission of NO will increase.

关 键 词：涡轮燃烧室 涡轮叶间补燃室 超紧凑燃烧室 径向槽 计算流体动力学 

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]