针对涡轮叶片尾缘吸力面热应力集中，容易造成叶片尾部烧毁的现象，提出端部冲击扰流柱结构，采用Realizable k-ε湍流模型和增强壁面函数分析涡轮叶片尾缘内部流场和吸力面换热特性，研究不同冲击孔与扰流柱排列方式的影响，揭示端部冲击扰流柱结构的流场与换热机理。研究表明，端部冲击扰流柱结构对于改善吸力面的换热效果要优于中间冲击扰流柱结构，对端壁的换热有显著提高；各表面平均换热系数均随着压比的增大而增大，顺排结构时，冲击孔换热最强，扰流柱换热次之；叉排结构时，冲击孔换热最强，隔板迎风换热次之；近距离冲击，顺排的综合效果优于其它几种结构，而远距离冲击，叉排的综合效果最好，其吸力面温度分布较均匀。

This paper mainly investigates on thermal stress concentration for the turbine blade trailing edge that it is easy to burn out the suction trailing edge of the turbine blade, so it’s significant to put forward the idea of the endwall impingement cylinders. Both Realizable k-ε Turbulence Models and Enhanced Wall Functions are used to analyze the inside flow fields of the trailing edge of turbine blade and investigate the heat transfer characteristics of the suction wall. It investigates on the influence of the different arrangement between impingement holes and cylinders. To reveal the flow field and heat transfer mechanism of the impingement cylinders. The results show that the endwall impingement cylinders’s heat transfers are better than the intermediate impingement cylinders on the suction surface, and it is significant to enhance the heat transfer of the endwall. The average heat transfer coefficients increase with the pressure ratios increase on the each surface. The heat transfer of the impingement holes are the strongest and the better is cylinders when in-line, the heat transfer of the impingement holes are the strongest and the better is the front partition when staggered. The comprehensive effects are better than other structures when in-line at the near-distance impingement, the staggered is the best at the long-distance impingement, and the suction surface temperature distributions are more uniform.

V232.4

国家自然科学基金（5167041385），陕西省教育厅专项科研计划项目（16JK1611）