为了提高尾缘冷却效果和降低叶栅气动损失，采用SST k-ω模型研究简化的压力面射流冷却结构唇板构型对冷却效果的影响。结果表明：唇板改型可以提高射流出口段的传热强度，但会增大气动损失；在研究范围内抬升一倍下板尾部边界层厚度时综合效果最佳；速比0.5和1.0时，原型的射流出流后向上抬升，在下板表面附近产生低速区，降低当地传热强度；速比0.5时，原型下板尾缘出现分离区，并与板后的回流区发生掺混，改型结构增强射流刚性，分离点后移；改型结构在不同速比下的传热系数均有所增强，平均传热系数在3个速比下分别提高了26.31%、34.72%和15.33%，其中速比1.0的综合传热因子最高，传热系数增加的幅值最大，且总压损失增加不显著。

The pressure side cutback is a typical cooling structure at turbine blade trailing edge,which can improve the cooling effect of the trailing edge and reduce the aerodynamic losses of the cascade.In this paper,the SST k-ω model is used to study the effect of lip configuration on cooling effect on a simplified jet cooling model.The results show that the lip designed in this paper can increase the heat transfer intensity after the jet exit,but it will increase the aerodynamic loss.It is found that there is an optimal lift height to make the best comprehensive effect.In this study,the optical lift height is the boundary layer thickness at the end of lower plate surface.When the velocity ratio(VR) is 0.5 and 1.0,the ejects of baseline model after the exit rise upwards,a low velocity zone is generated near the lower plate surface and the local heat transfer intensity is reduced.When the VR is 0.5,the separation zone appears at the baseline model trailing edge of the lower plate surface and mixes with the recirculation zone behind the plate.The modified lip structure enhances the rigidity of the jet and the separation point moves backward.The average heat transfer intensity of the modified lip structure at three velocity ratios has been increased by 26.31%，34.72% and 15.33%,respectively.The VR of 1.0 generates the best performance: the amplitude of the increase in heat transfer is the largest,and the loss increase is not significant.

TK471