边倒圆型气膜孔流动换热特性研究  

Experimental and Numerical Study on Film Cooling Performance of Radiusing-Type Hole

作　　者：孟通[1] 朱惠人[1] 刘存良[1] 周申平 MENG Tong;ZHU Hui-ren;LIU Cun-liang;ZHOU Shen-ping(School of Power and Energy, Northwestern Ploytechnical University, Xi ＇an 710072, China;AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《推进技术》2018年第5期1067-1076,共10页Journal of Propulsion Technology

基　　金：国家重点基础研究发展计划资助项目(2013CB035702)

摘　　要：为提高涡轮叶片气膜冷却效率,根据主流与射流间的相互作用关系,并以圆柱型气膜孔为基础,在气膜孔出口前缘位置进行边倒圆处理,同时对该新型的边倒圆型气膜孔结构进行了实验及数值计算研究。分析了边倒圆型气膜孔的流动换热机理,得到了新型气膜孔下游全表面气膜冷却特性分布及气膜孔的流量系数。结果表明:边倒圆型气膜孔内流动均匀,出口涡强度有所降低,进而能够减弱主流通道内的反转对涡强度;同时由于边倒圆孔的扩张作用使得射流法向动量降低、展向动量增强,从而提高气膜冷却效率。边倒圆型气膜孔的孔下游区域气膜贴壁性较好,气膜展向覆盖面积较大。相比于圆柱型气膜孔,边倒圆型气膜孔下游区域换热系数较高,远孔区域换热系数较小。新型气膜孔的流量系数比圆柱型气膜孔约大5%,孔内流动损失较小。整体上看,边倒圆型气膜孔具有较好的流动换热特性。In order to get higher film cooling performance, a new structure called radiusing-type hole was proposed based on cylinder hole and the interaction between mainstream and jet of film cooling. Medication of radiusing was used near the leading edge of film cooling hole. Experiments and numerical simulations were conduct- ed to figure out the flow and heat transfer performance of radiusing-type hole. Film cooling characteristics down- stream of the hole and discharge coefficient were studied. Results show that flow structure within the radiusing-type hole is more uniform than cylindrical hole which leads to weaker kidney vortex pairs in main flow. Normal momentum of jet is weaker and lateral momentum is stronger because of the expanding effect of radiusing-type hole, these two factors improve film cooling performance. For radiusing-type hole, the film attach on the wall bet- ter and cover wider area. In the region downstream the exit of radiusing-type hole, heat transfer coefficient is high, along the stream wise direction heat transfer coefficient is sharply decreased. The discharge coefficient of ra diusing-type hole is 5% higher than cylindrical hole. In general, radiusing-type hole has better flow and heat transfer characteristics.

关 键 词：涡轮叶片 气膜冷却 边倒圆型气膜孔 实验研究 数值模拟 

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]