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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。
The load of modern aviation gas turbines increases, the Mach number in the runner increases, the shock loss increases, the flow entropy increases, the aerodynamic efficiency decreases, and the energy loss increases. In the high-power and high-load aviation gas turbine, the impact of shock wave on aerodynamic performance is more obvious. In this paper, the turbine blade design of aeroengine was retrofitted, the structure of the shock at different exit Mach numbers was analyzed, and the method of reducing the blade loss by controlling the shock intensity was studied. The study found that the suction side of the leaf with a curved arc of curvature for the control of shock intensity, reduce the energy loss obvious.