为探究不同气动参数对涡轮工作叶片冷却性能的影响，通过试验研究了中温中压工况下高压涡轮工作叶片综合冷却效果分布，主要讨论燃气与冷气的温比、冷气与燃气的质量流量比和栅后雷诺数对综合冷却效果的影响。试验温比变化范围为1.3~2.1，质量流量比变化范围为0.002~0.02，栅后雷诺数变化范围为2.9×105~4.8×105。结果表明：不同气动参数下，综合冷却效果较低位置出现在叶片前缘和尾缘，较高冷却效果出现在叶背1/4和1/2相对弧长位置；当质量流量比从0.008增加到0.014、温比分别为1.40，1.67和1.90时的综合冷却效果分别提高了44.4%，44.5%和34.4%；当温比从1.8增加到2.1、质量流量比为0.008，0.011和0.015时的综合冷却效果分别降低了3.6%，1.6%和4.2%；当栅后雷诺数从2.9×105增加到4.8×105、温比为0.011、质量流量比为167时，综合冷却效果降低了20.7%。

To explore the influence of different aerodynamic parameters on the cooling performance of turbine blade, the overall cooling effectiveness distribution of highpressure turbine blade under medium temperature and medium pressure was studied experimentally. The effects of the gastocoolant temperature ratio, the coolanttogas mass flow ratio and the outlet Reynolds number of the cascade on the overall cooling effectiveness of blade were mainly discussed. The temperature ratio varies from 1.3 to 2.1, the mass flow ratio is from 0.002 to 0.02, and the outlet Reynolds number of the cascade goes from 2.9×105 to 4.8×105. The experimental results show that under different aerodynamic parameters, the lower overall cooling effectiveness appears at the leading and trailing edges of the blade, and the higher appears at the 1/4 and 1/2 relative arc length of the blade convex; when the mass flow ratio increases from 0.008 to 0.014, and the temperature ratios are 1.40, 1.67 and 1.90, the corresponding overall cooling effectiveness is increased by 44.4%, 44.5% and 34.4%, respectively; when the temperature ratio varies from 1.8 to 2.1, the overall cooling effectiveness decreases by 3.6%, 1.6% and 4.2%, corresponding to the mass flow ratio of 0.008, 0.011 and 0.015; when the outlet Reynolds number of the cascade goes from 2.9×105 to 4.8×105, the temperature ratio is 0.011 and the masstoflow ratio is 1.67, the overall cooling effectiveness is reduced by 20.7%.

TK47

国家自然科学基金（52376028）；辽宁省自然科学基金（2023MS245）；辽宁省教育厅面上项目（LJKMZ20220541）