涡轮叶片前缘压力面侧孔排气膜冷却特性研究  

Study on the Film Cooling Characteristics of the Hole Rows on the Pressure Side of Turbine Blade Leading Edge

作　　者：吴星学 李广超 WU Xing-xue;LI Guang-chao(Department of Aero engine of Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学航空发动机学院,辽宁沈阳110136

出　　处：《山东工业技术》2022年第4期3-9,共7页Journal of Shandong Industrial Technology

基　　金：国家科技重大专项(2017-III-0001-0025);辽宁省创新人才计划(LR2019050);辽宁省教育厅项目(JYT19062)。

摘　　要：采用红外热像仪研究了涡轮叶片前缘压力面侧孔排在吹风比为1.0~2.0、雷诺数为4×105~8×105时的气膜冷却特性。结果表明:气膜孔出口面积大,冷气出流速度相对较低。气膜对壁面的附着性提升,孔下游气膜冷却效率高。K2排孔的展向平均气膜冷效在各吹风比下分别比K1排孔高71%、71.4%和36.8%。叶片前缘压力面侧孔排形成的气膜较短,展向覆盖不连续。The film cooling characteristics of hole rows on the pressure side on the leading edge of turbine blade at blowing ratio of 1.0-2.0 and Reynolds number of 4×105~8×105 were studied by infrared thermal imager.The results show that the outlet area of the film holes is large,and the outflow velocity of the coolant is relatively low.The film adhesion to the wall is improved,and the film cooling effectiveness downstream of the holes is high.The spanwise average film cooling effectiveness of K2 row holes is 71%,71.4%and 36.8%higher than that of K1 row holes under each blowing ratio.The film formed on the pressure side hole rows on the leading edge of the blade is short and the spanwise coverage is discontinuous.

关 键 词：叶片前缘 雷诺数 气膜冷却效率 全表面温度测量 吹风比 换热系数 

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]