【摘要】 针对航空发动机高压涡轮实际运行工况中来流和涡轮叶片表面的巨大温差，本文以典型凹槽叶顶结构为研究对象，综合考虑静止和机匣高速相对运动条件，开展不同主流–壁温温度比对叶顶表面气动换热特性的影响研究。以课题组实验结果作支撑，对比分析温度比0.6和0.9的数值模拟结果。研究结果表明，随温度比降低，叶顶换热系数明显增加，特别是在机匣相对运动条件下更为明显；凹槽内部和机匣壁面附近流体密度增大，黏度减小，雷诺数明显增加，使得凹槽内旋涡结构位置和尺度发生变化，进一步影响泄漏流动。更多还原

【Abstract】 For realistic operating condition in high-pressure turbine of aeroengine, there are huge temperature differences between in-coming flow and turbine blade surface. This paper conducted the research on the effect of wall-to-gas temperature ratio on blade squealer tip heat transfer. On the basis of previous experimental results, the simulation results are compared for wall-to-gas temperature ratio of 0.6 and 0.9. It is shown that, as the wall-to-gas temperature ratio decreases, the heat transfer coefficient increases significantly, especially under the condition with relative casing motion.Around the cavity floor and casing surface, fluid density increases and dynamic vorticity decreases.Huge difference of local Reynold number happens, which changes the scale of vortex structures and rearranges their locations. This further influences the leakage flow around the tip gap.更多还原