尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究  

Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence

作　　者：李继宸 朱惠人[1] 陈大为 陈刚 周道恩 LI Jichen;ZHU Huiren;CHEN Dawei;CHEN Gang;ZHOU Daoen(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;AECC Shenyang Engine Institute,Shenyang 110015,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航发沈阳发动机研究所,沈阳110015

出　　处：《西安交通大学学报》2019年第9期167-175,共9页Journal of Xi'an Jiaotong University

基　　金：国家重点基础研究发展规划资助项目(2013CB035702)

摘　　要：为研究尾迹影响下带有复合角扇形孔的涡轮叶片的气膜冷却效率变化规律,利用压敏漆技术获得了不同质量流量比、不同尾迹斯特劳哈尔数(0、0.12、0.36)下的涡轮叶片表面气膜冷却效率分布。研究结果表明:气膜孔复合角有利于射流的横向扩散,孔下游射流的覆盖面积较大;在无尾迹条件下,质量流量比的增加使得带有复合角气膜孔的涡轮叶片前缘与压力面大部分区域的气膜冷却效率提高,使得吸力面气膜冷却效率下降,吸力面靠近叶顶的低气膜冷却效率区域面积变小;在尾迹条件下,质量流量比的增加使得前缘、压力面以及吸力面靠近尾缘区域的气膜冷却效率提高,使得吸力面其他区域的气膜冷却效率降低;尾迹会使叶片表面气膜冷却效率显著降低,在尾迹斯特劳哈尔数为0.36的条件下,小质量流量比时叶片表面气膜冷却效率的平均降幅为35%,大质量流量比时平均降幅为26%,气膜冷却效率的下降幅度减小。The film cooling effectiveness of the turbine blade with compound-angled fan-shaped holes was measured by the pressure sensitive paint technique. The wake’s Strouhal number was varied from 0 to 0.36 and three mass flux ratios were determined. Results show that the compound-angled holes can enhance the lateral spreading of coolant, and the injection has a wider coverage area without wakes. The increase of the mass flux ratio causes an increase in the film cooling effectiveness over the leading edge and most area of the pressure surface with compound-angled holes, but a decrease on the suction surface. The increase of mass flux ratio also reduces the area near the tip on the suction side, where the film coverage is insufficient under wake influence, and causes an increase in the film cooling effectiveness over the leading edge, the pressure surface and the suction surface near the trailing edge, but decreases this effectiveness on the mid-chord region of the suction surface. The wake causes a remarkable decrease in the film cooling effectiveness over the blade surface. In the case that wake’s Strouhal number is 0.36, the average film cooling effectiveness over the blade is decreased by 35% under the condition of low mass flux ratio, and decreased by 26% under the condition of high mass flux ratio.

关 键 词：复合角扇形孔 尾迹 气膜冷却效率 压敏漆 涡轮叶片 

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]