下缘板孔对涡轮叶片尾缘内冷通道流动换热影响的数值研究

Numerical Study on Effect of Lower Edge Plate Hole on Flow and Heat Transfer of Internal Cooling Passage in Trailing Edge of Turbine Blades

摘要:

涡轮叶片下缘板出气孔对内冷通道的流动和换热性能有较大影响。通过数值模拟方法研究下缘板出 气孔对尾缘和下缘板双路出气涡轮叶片尾缘内冷通道内的流动和换热特性,对比分析孔径、孔形和孔位置对尾 缘溢流孔流量系数、尾缘出流比、尾缘通道内总压系数和尾缘内冷腔壁面换热特性的影响。结果表明:下缘板 出气孔孔径对流量系数分布的影响显著,孔径增大,尾缘溢流孔流量系数下降,尾缘出流比减小,尾缘内冷通道 内压力损失降低,内冷腔平均换热系数增大;孔形对上游内冷通道内流动和换热几乎没有影响;孔位置变化对 内冷通道壁面整体的换热系数影响很小,对局部影响较大。

Abstract:

To explore the influence of the lower edge plate hole of the turbine blade on the flow and heat transfer of the internal cooling passage on the upstream trailing edge side, the numerical analysis of the turbine blade from the trailing edge and the lower edge plate was carried out. The effects of hole size, hole shape and hole position of the lower edge plate on the distribution of the flow coefficient of the overflow hole in the trailing edge, the outflow distribution from the trailing edge and the lower edge plate and the heat transfer of the internal cooling passage wall were analyzed. The results showed that: (1) The distribution of the hole flow coefficient of the lower edge of the plate had a significant effect. The hole diameter increased, the flow coefficient of the overflow hole of the trailing edge decreased. (2) The hole diameter increased, the tailing edge outflow ratio decreased, the pressure loss in the cold passage in the trailing edge decreased, and the average heat transfer coefficient of the internal cooling passage increased. (3) The shape of the hole had small effect on the flow and heat transfer in the upstream inner cold passage. (4) The change of the hole position had small effect on the heat transfer coefficient of the inner wall of the inner cold passage, and had a great effect on the local.