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利用短周期风洞,在发动机典型雷诺数和马赫数状态下对MarkII叶型进行了表面换热测量;用基于一维半无限假设的脉冲响应法将测量的表面温度处理为热流密度,并用最小二乘法得到主流绝热壁温和表面换热系数。实验结果与国外文献使用稳态实验方法获得的结果基本一致。对数据处理方法进行了详细的误差分析,并将二维瞬态热分析法与脉冲响应法进行了对比,表明在叶片前缘曲率较大处、尾缘壁厚较薄处和换热系数剧烈变化处,一维半无限大假设条件遭到破坏,脉冲响应法的计算结果存在偏差。
The short-period wind tunnel was used to measure the surface heat transfer of Mark II airfoil under the typical engine Reynolds number and Mach number. The measured surface temperature was treated as the heat flux density by impulse response method based on one-dimensional and semi-infinite assumptions, The second multiplication gives the mainstream heat insulation wall mild surface heat transfer coefficient. The experimental results are consistent with the results obtained from the steady-state experimental methods in foreign literature. A detailed error analysis of the data processing method is carried out. The two-dimensional transient thermal analysis method and impulse response method are compared. It shows that when the curvature of the leading edge of the blade is large, the thickness of the trailing edge is relatively thin and the heat transfer coefficient is high Variations, one-dimensional semi-infinite assumptions have been damaged, impulse response method of calculating the results of the existence of bias.