A new numerical method for predicting the profileloss of turbine blades in subsonic and supersonic flows is presented.
给出了一个计算亚、跨音涡轮叶栅叶型损失的数值计算方法。
2
Thus, the aerodynamic performance of stage is im-proved obviously, the profileloss decreases through using the "after loading" blade.
优化的“后部加载”叶型明显提高了气动性能，降低了叶型能量损失。
3
It is proved that the profileloss can be decreased with the use of advanced blade through the comparison of loss coefficient of blade surface overall pressure.