涡轮叶片前缘冲击-气膜冷却流动传热实验  

Experiment on Flow and Heat Transfer of Impingement-Film Cooling for Leading Edge of Turbine Blade

作　　者：阎鸿捷 陈冠江 饶宇[1] YAN Hong-Jie;CHEN Guan-Jiang;RAO Yu(Institute of Turbomachinery,School of Mechanical Engineering,Shanghai Jiao Tong University,Shanghai 200240,China)

机构地区：[1]上海交通大学机械与动力工程学院,叶轮机械研究所,上海200240

出　　处：《工程热物理学报》2020年第12期2970-2976,共7页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.51676119,No.11972230)。

摘　　要：本文采用瞬态液晶热像技术对涡轮叶片的前缘冲击-气膜复合冷却结构内部传热性能进行了详细实验研究。通过优化改进瞬态液晶热像测试技术实现了对前缘曲率表面传热的可靠准确测量,获得了雷诺数20000~50000范围内内前缘冲击-气膜冷却内部详细传热分布和该复合冷却流阻特性。结果表明:冲击-气膜冷却的努塞尔数和压力损失均随雷诺数的增大而增大;冲击孔偏置使得内部表面平均努塞尔数最多提高9.4%,阻力系数下降约6.0%,且换热的均匀性得到显著提升。Detailed experiments using transient liquid crystal thermal imaging technique were conducted to study the internal heat transfer characteristics of impingement-film cooling for leading edge of gas turbine blade.The transient liquid crystal thermal imaging technique was modified to accurately measure the heat transfer of curved surface of leading edge.The detailed internal heat transfer distribution and flow resistance characteristics were obtained with Reynolds number ranging from 20000 to 50000.Experimental results show that both the Nusselt number and flow resistance coefficient increase as Reynolds number increases.The offset of jet holes can increase the overall average Nusselt number by 9.4%at most and decrease the flow resistance coefficient by about 6%.Meanwhile,the uniformity of internal heat transfer is improved.

关 键 词：涡轮叶片冷却 前缘冲击-气膜冷却 热色液晶(TLC) 旋流 

分 类 号：TK124[动力工程及工程热物理—工程热物理]