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以带有复合冷却结构的涡轮叶片为基础模型,对有/无热障涂层保护下的叶片冷却效果进行了气热耦合数值计算,并通过改变热障涂层的厚度研究了热障涂层对叶片换热的影响规律。研究发现:带有热障涂层的叶片温度明显下降,且越靠近叶片前缘处,温度降低幅度越大;随着热障涂层厚度的增加,下降趋势逐渐变慢;与无热障涂层时叶片温度相比,叶片前缘区域温降最大,当热障涂层厚度为0.35mm时,温降高达160K,压力面和吸力面与前缘相比温降程度较低。
Based on the turbine blade with composite cooling structure, the numerical calculation of the cooling effect of the blade under the protection of / without thermal barrier coating was carried out. The thermal barrier coating was studied by changing the thickness of the thermal barrier coating Effect on heat transfer of leaves. The results show that the temperature of the blade with thermal barrier coating drops obviously, and the temperature decreases more when it approaches the leading edge of the blade. As the thickness of the thermal barrier coating increases, the descending trend becomes slower. When the thickness of thermal barrier coating is 0.35mm, the temperature drop is as high as 160K, and the pressure drop and suction surface are lower than the leading edge.