中文摘要：

本文在环形叶栅端壁30％、60％、90％轴向弦长处和距前缘-10％轴向弦长端壁处布置多排圆柱形气膜冷却孔，运用CFD方法在吹风比为1．0条件下，模拟分析端壁气膜冷却效率。结果表明，叶片两侧各有一支马蹄涡夹裹冷却气膜主体向吸力面偏移，致使压力面一侧端壁未冷却区域扩大，吸力面一侧端壁未冷却区域缩小。吸力面一侧端壁气膜冷却效率沿流向逐渐提升，并在流道中、下游完全冷却覆盖端壁，而压力面一侧端壁一直未能获得冷却气膜覆盖。在压力面壁角内增设冷却气膜孔，改进了壁角的冷却效果，消除了局部壁面超温的问题。

英文摘要：

Multi-rows of cylinder film cooling holes were allocated at 30, 60, 90 percent of axial blade chord and 10 percent upstream of leading edge respectively on the endwall of an annular turbine cascade. Endwall cooling effectiveness was analyzed with CFD techniques for the film blowing ratio of 1.0. Results showed that two branchs of horse-shoe vortex around the airfoil enrolled the endwall film fluids and moved toward the blade suction side（SS）. The uncooled endwall region near pressure side （PS） was enlarged while near SS is suppressed. Film effectiveness along SS was increased gradually to cover the mid and aft passage endwall. However, the PS endwall region was exposed without cooling. Extra film holes were allocated along the PS corner to improve the local cooling effects. The endwall over-heat pots were finally solved.