本文用数值方法计算了无气膜冷却涡轮叶片上包括前驻点的整个型面上的换热系数。
Several problems involved in the prediction of heat transfer coefficient on the turbine blade profiles without film cooling are studied in this paper for the purpose of improving the accuracy.
计算结果表明：驻点温度随热防护层厚度的变化并不明显，而冷却系统功率随热防护层厚度增加急剧降低；
The results indicate that the thickness variations exhibit no significant influence on stagnation temperature, while the cooling power drops sharply as the thickness increases.
计算结果表明：驻点温度随热防护层厚度的变化并不明显，而冷却系统功率随热防护层厚度增加急剧降低；
The results indicate that the thickness variations exhibit no significant influence on stagnation temperature, while the cooling power drops sharply as the thickness increases.
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