端壁转动对凹槽叶尖流动换热性能的影响  

Effects of End-Wall Rotation on Aerothermal Performance of Squealer Tip

作　　者：皮骏 杜旭博 孔庆国[3] 刘光才 PI Jun;DU Xu-bo;KONG Qing-guo;LIU Guang-cai(College of General Aviation,Civil Aviation University of China,Tianjin 300300,China;School of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学通用航空学院,天津300300 [2]中国民航大学航空工程学院,天津300300 [3]中国民航大学中欧航空工程师学院,天津300300

出　　处：《推进技术》2019年第5期1005-1014,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金委员会与中国民用航空局联合资助(U1633101);中央高校基本科研业务费民航大学专项基金(3122013H001)

摘　　要：为了研究端壁转动对跨声速凹槽叶尖流动换热性能的影响,采用数值方法,详细研究了三种冷却孔结构凹槽叶尖在端壁转动条件下的叶尖间隙流场、冷却流流态、气膜冷却效率、叶尖表面换热系数和叶尖泄漏流量,同时考虑凹槽深度和端壁转动速度的影响。结果表明:端壁转动在叶尖凹槽内形成与泄漏流分离涡方向相反的旋涡,使泄漏流在凹槽底面的再附增强,在凹槽突肩的再附减弱。端壁转动能减少叶尖泄漏流量,研究范围内,叶尖相对泄漏流量最多减小20%。随着凹槽深度增大,叶尖平均气膜冷却效率随之增大,叶尖平均换热系数和叶尖泄漏流量随之减小。随着端壁转速减小,叶尖泄漏流量随之增大,压力侧和吸力侧冷却孔模型的叶尖平均气膜冷却效率随之减小,而中弧线冷却孔模型的叶尖平均气膜冷却效率随之增大。压力侧喷入冷却气流,叶尖的气膜冷却效果最好。In order to investigate the effects of end-wall rotation on aerothermal performance of transonic squealer tip,the flow field,cooling injection behavior,cooling effectiveness,tip heat transfer and over tip leakage flow rate of the squealer tip with three different cooling configurations under end-wall rotation were in detail studied use a numerical method.The effects of squealer depth and rotation velocity were also considered.The results show that the end-wall rotation forms a vortex opposite to the direction of the leakage flow separate vortex within the tip squealer,the reattachment of leakage flow on the squealer floor increases,and the reattachment of leakage flow is decreased at the squealer rim inversely.The rotation of the end-wall can reduce the over tip leakage flow,and the maximum decrease is up to 20%at the research range relatively.With the increase of squealer depth,the average film cooling efficiency of squealer tip increases,the average heat transfer coefficient and the over tip leakage flow ratio of the blade tip decreases accordingly.With the decrease of the rotation speed,the over tip leakage flow ratio increases,the average film cooling efficiency of squealer tip on pressure side and the suction side cooling model decreases,the average film cooling efficiency of squealer tip on camber line cooling model increases inversely.Pressure side film cooing model have the best cooling effectiveness on squealer tip.

关 键 词：高压涡轮 叶尖凹槽 端壁转动 换热系数 叶尖泄漏流 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]