涡轮叶片尾缘劈缝结构换热特性试验研究  

Experimental Investigation on Heat Transfer Characteristics of Turbine Blade Trailing Edge Cutback

作　　者：李杰 陶一鸾 孙瑞嘉 钟滨涛 杨卫华[1] LI Jie;TAO Yiluan;SUN Ruijia;ZHONG Bintao;YANG Weihua(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Shenyang Engine Design and Research Institute,Shenyang 110015,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中航工业沈阳发动机设计研究所,沈阳110015 [3]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《重庆理工大学学报（自然科学）》2020年第1期185-194,共10页Journal of Chongqing University of Technology：Natural Science

基　　金：国家自然科学基金资助项目(51276088)

摘　　要：为研究涡轮叶片尾缘劈缝结构的换热特性,设计了6种劈缝结构,采用试验的方法分别对其绝热冷却效率与对流换热系数的影响规律进行研究,研究表明:①随着吹风比的增加,绝热冷却效率和对流换热系数均呈现逐渐增大的趋势;②劈缝出流角度对尾缘区域的气膜冷却特性有很大影响,随着尾缘劈缝出流角度的增加,尾缘绝热冷却效率逐渐升高,对流换热系数逐渐降低;③劈缝出口固体壁面形状对尾缘气膜冷却特性有很大影响,劈缝出口固体壁面为圆角的尾缘绝热冷却效率最高,随着劈缝分隔壁长度的减小,绝热冷却效率逐渐减小,对流换热系数逐渐升高。In order to study the heat transfer characteristics in trailing edge cutback of turbine blade,six kinds of test pieces of trailing edge were designed. The influence of its adiabatic cooling effectiveness and convective coefficient was investigated by experiment. The experimental result shows that the adiabatic cooling effectiveness and convective coefficient at the same position of trailing edge increased gradually with the increase of blowing ratio. And the flow angle has a great influence on the film cooling characteristics of trailing edge cutback, with the increase of the flow angle, the adiabatic cooling effectiveness of trailing edge increases and the convective coefficient decreases gradually. The shape of solid wall at the outlet has a great influence on the film cooling characteristics of trailing edge cutback, the adiabatic cooling effectiveness is the highest when the shape of solid wall at the outlet is rounded corner, with the decrease of the length of the partition, adiabatic cooling effectiveness decreases and convective coefficient increases gradually.

关 键 词：涡轮叶片 劈缝 绝热冷却效率 对流换热系数 吹风比 

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]