为探究高空低雷诺数下旋转效应对涡轮共转盘腔内的流动换热特性影响,数值模拟计算了冲击雷诺数为1×103、旋转雷诺数0~8.8×105下的工况,并分析共转盘腔内流场结构和换热系数分布。结果表明:低旋转雷诺数下射流能够有效冲击到靶面,高旋转雷诺数下射流不能有效冲击到靶面。靶面恢复温度沿着径向分布较为均匀,旋转雷诺数从0增加到8.8×105,靶面平均恢复温度升高45K,靶面平均换热系数提高77%。随着径向位置增大,靶面换热系数先增大后减小,靶面r/d=0.81处换热系数最大。

To investigate the effect of rotation on the flow and heat transfer characteristics in a turbine co-rotating disk cavity at high altitude and low Reynolds numbers, numerical simulations were conducted to calculate an impact Reynolds number of 1 × 103. Rotating Reynolds number 0~8.8 × 105, the flow field structure and heat transfer coefficient distribution of the co rotating disc cavity. The results indicate that the jet can effectively impact the target surface at low rotational Reynolds numbers, but cannot effectively impact the target surface at high rotational Reynolds numbers. The recovery temperature of the target surface is evenly distributed along the radial direction, and the rotational Reynolds number increases from 0 to 8.8 × 105, the average recovery temperature of the target surface increased by 45K, and the average heat transfer coefficient of the target surface increased by 77%. As the radial position increases, the heat transfer coefficient on the target surface first increases and then decreases, with the maximum heat transfer coefficient at r/d=0.81 on the target surface.

辽宁省自然科学基金