本文针对涡轮叶片离散气膜孔结构及叶片表面具有不同曲率的特点 ,采用传质比拟、数值计算及可视化技术 ,通过比较平板、弯曲壁面及涡轮叶片的气膜冷却流动及传热特性 ,系统地研究了离散孔三维效应、壁面曲率及压力梯度诸因素对叶片气膜冷却的影响。在此基础上 ,提出了估算叶片头部、中弧区及尾缘气膜冷却有效温比的准则公式、实验曲线及计算机程序 In this paper, according to the characteristics of discrete gas film pore structure and different curvature of blade surface of turbine blade, by mass transfer, numerical calculation and visualization technology, by comparing the film cooling flow and heat transfer characteristics of slab, curved wall and turbine blade, The effects of three-dimensional effect of discrete pores, wall curvature and pressure gradient on the film cooling of the blade were studied. On this basis, the criterion formula, experimental curve and computer program for estimating the effective temperature ratio of air film cooling at the blade head, the arc zone and the trailing edge