尾缘喷气方式对涡轮叶栅气动性能的影响

以某涡轮叶栅为研究对象,采用试验和数值模拟相结合的方式研究了涡轮叶片不同喷气结构对叶栅性能的影响。对半开缝和对开缝两种尾缘冷气喷射的研究表明:当冷气流量比较小时,有一个总压损失随冷气量增大先增加后减小的趋势:当冷气量较大时,冷气造成的总压损失随冷气增大而减小。在相同条件下,半开缝叶栅出口的总压损失系数小于对开缝叶栅出口的总压损失系数。叶栅出口平均气流角随着喷气比的增大呈减小的趋势,但变化范围很小。

Aerodynamic effect of turbine blade trailing edge ejection on turbine cascade

Numerical simulations and tests were carried out to investigate the effect of ejection from different trailing edge slots of a turbine cascade.The results show that the total pressure loss coefficient increases at first and then it has a decreasing tendency with the increase of ejection ratio.The total pressure loss coefficient for the ejection through the trailing edge slot would be higher than that for the ejection on the pressure side near the trailing edge.The exit flow angle of the two slot types has a little decrease with the increase of ejection ratio.