本文采用数值模拟的方法对凹槽叶顶前缘气膜孔的位置进行了研究,通过改变前缘第一气膜孔位置来分析叶顶区传热。数值模拟结果表明,由于冷却气对该区域没有提供足够的保护,肩壁表面的平均绝热效率远低于凹槽底面,平均传热系数远高于凹槽底面。叶顶第一气膜孔向前缘移动使肩壁表面的平均传热系数先升高再降低,叶顶前缘低绝热冷却效率区逐渐消失。 In this paper, the numerical simulation method is used to study the position of the film hole in the leading edge of the groove. The heat transfer in the tip area is analyzed by changing the position of the first film hole in the leading edge. The numerical simulation results show that the average adiabatic efficiency of the shoulder surface is much lower than the bottom of the groove and the average heat transfer coefficient is much higher than the bottom of the groove because the cooling gas does not provide sufficient protection for the area. The first film hole at the top of the blade moved to the front edge of the hole so that the average heat transfer coefficient of the shoulder wall first increased and then decreased, and the area of ​​low adiabatic cooling efficiency gradually disappeared.