cascade with low profile loss 低型损叶栅
profile mismatch loss 分布失配损耗
refractive-index-profile mismatch loss 折射率分布失配损耗
A new numerical method for predicting the profile loss 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。
Thus, the aerodynamic performance of stage is im-proved obviously, the profile loss 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。
It is proved that the profile loss can be decreased with the use of advanced blade through the comparison of loss coefficient of blade surface overall pressure.
通过叶片表面总压损失系数,证实了先进叶型在流动中可以降低叶型损失。
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