尾缘冷却跨声速涡轮气动特性的数值模拟

Numerical simulation of the trailing edge cooled transonic turbine aerodynamic characteristic

关键词:  跨声速涡轮叶栅  尾缘冷却  冷却流量  尾缘激波系  叶栅性能

Key words:  Transonic turbine cascade  Trailing edge cooling method  Coolant mass flow  Trailing edge shock system  Cascade performance

摘要:

为了明确跨声速涡轮中尾缘冷却措施的引入对其气动性能的影响,针对跨声速涡轮叶栅中压力面半劈缝尾缘冷却方式和尾缘全劈缝冷却方式条件下,叶栅性能和尾缘激波系结构的变化进行了数值研究。结果显示,两种尾缘冷却措施都降低了叶栅能量损失系数,压力面半劈缝尾缘冷却方式效果更好,最佳情况损失系数下降达到48%。冷却流量对作用效果有一定影响,存在最佳值。冷却措施的引入显著改变了尾缘激波系结构,尤其对PSEJ冷却方式,将尾缘激波系压力面分支由原本一道强激波分成三道弱激波。

Abstract:

To find out the effect of the cooling method on aerodynamic characteristic in transonic turbine,the influence of the two kinds of transonic turbine cascade trailing edge cooling methods,pressure side ejection (PSEJ) and trailing edge ejection (TEEJ),on the cascade performance and trailing edge shock system structure has been researched in numerical simulation.The results indicate that,both methods reduce the cascade energy loss coefficient.The PSEJ style has better effect,and for the optimal case,the loss coefficient decreases up to 48%.The coolant mass flow has effect to some extent and there is a optimal value.The introduction of the trailing edge cooling changes the trailing edge shock system obviously,especially for the PSEJ method.The previous pressure side leg of the shock system has been split to three legs.