中文摘要：

现代航空燃气轮机负荷升高，流道内马赫数提高，激波损失增大，流动熵增增加，气动效率下降，能量损失增加。在大功率高负荷航空燃气轮机中，激波对气动性能影响更加明显。本文对某型航空发动机涡轮叶型进行了改型设计，分析了在不同出口马赫数条件下激波的结构，研究了通过控制激波强度以减小叶型损失的方法。研究发现，吸力侧带有反曲率弧段的叶型对于控制激波强度、减少能量损失作用明显。

英文摘要：

As the load of modern aviation gas turbine increases, the Mach number in the blade passage increases, so the shock wave losses and the entropy production increases. That results in the decrease of aerodynamic efficiency and the increase of energy loss. The effects of shockwave on the aerodynamic characteristic are more evident in highly loaded aviation gas turbines. This paper made an improvement on blades of a real aviation gas turbine, analyzed the structure of the shock wave on different outlet Mach number, and researched the measure to decrease the profile loss by controlling the shock wave intensity. The result shows that the negative curvature design can reduce the intensity of the shock wave and the loss of the energy loss remarkably.