论文部分内容阅读
基于相似理论,对简化的层板冷却涡轮叶片前缘放大模型内部的流动与传热特性进行实验研究,对比了无绕流柱和带菱形扰流柱两种实验模型的流动阻力系数、靶面温度和表面传热系数的分布.实验中采用红外热像技术测量换热面的温度,采用ANSYS软件计算换热面的局部热流密度.结果表明:两种模型的流动阻力随进气雷诺数逐渐增大,带菱形扰流柱模型的流动阻力总体上较大;靶面局部表面传热系数的分布特征基本相同,带菱形扰流柱模型的局部表面传热系数比无扰流柱模型的稍高;靶面平均表面传热系数的差别很小,相同进气雷诺数下带菱形扰流柱模型的平均表面传热系数值最多大7%.
Based on the similarity theory, the flow and heat transfer characteristics of a simplified laminar cooling turbine blade leading edge model are experimentally studied. The flow resistance coefficients of the two models with no flow around the column and the rhombic flow column are compared. Temperature and surface heat transfer coefficient.The temperature of the heat transfer surface was measured by infrared thermography and the local heat flux density was calculated by ANSYS software.The results showed that the flow resistance of the two models gradually increased with the Reynolds number The flow resistance of the model with rhombic spoiler is larger than that of the non-interfering column model. The distribution characteristics of the local surface heat transfer coefficient are basically the same, and the local surface heat transfer coefficient of the rhombus- The average surface heat transfer coefficient of the target surface is very small. The average surface heat transfer coefficient at the same inlet Reynolds number with the rhombic spoiler model is at most 7% larger.