针对涡轮叶片红外测温探头测量开口背对燃气时热防护性能不足的问题,采用CFD方法模拟计算了探头保护套底部开设气膜孔对热防护的强化效果。研究了气膜孔数及气膜孔直径对探头热防护性能的影响规律,分析了保护套壁面温度分布及气膜覆盖特性,并探究了热防护性能产生差异原因。结果表明,随着气膜孔数或气膜孔直径的增加,探头保护套底部的气膜覆盖程度逐渐增大,保护套最高温度从探头底部转移到了探头侧面,且呈现出先降低后升高的变化特性；探头保护套热防护的最佳气膜孔数为5个,最佳气膜孔直径为1.5mm,比无气膜热防护最高温度降低187K；探头保护套内部侧面近壁区冷却空气的对流换热是影响探头保护套侧壁面温度的主要因素。

This article focuses on the problem of poor thermal protection when the opening of infrared temperature probe for turbine blades toward to the gas flow direction. The CFD method was used to simulate and calculate the thermal protection strengthening effect when drilling film holes at the bottom of the probe protective sheath. The influence of the number and diameter of film holes on the thermal protection performance of the probe was studied. The results showed that the air film coverage extent at the bottom of the probe protective sheath gradually increased with the increases of the number or the diameter of air film holes. And the highest temperature of the protective sheath shifted from the bottom of the probe to the side of the probe, which showed a change characteristic of first decreasing and then increasing. The optimal number of air film holes for thermal protection of the probe protective sheath is 5, and the optimal diameter of gas film holes is 1.5mm, which maximum temperature is 187K lower than the maximum temperature without air film thermal protection. The convective heat transfer of the cooling air near the wall inside the probe protective sheath is the main factor affecting the temperature of the side wall of the probe protective sheath.

TK124

中国科学院科研仪器设备研制项目