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。
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.
分析在不同叶片安装角下，叶片表面静压系数、出口总压损失系数和出口气流角的变化规律。
The static pressure loss coefficients, total pressure loss coefficients and flow outlet Angle distribution are simulated in conditions of different setting angles.
经优化后，透平高压级静叶的总压损失系数减少0.95%；多级压气机整机效率提高2.1%。
After optimization, the total pressure loss of the turbine vane was reduced by 0.95%, and the efficiency of the overall compressor was increased by 2.1%.
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