亚声速压气机平面叶栅雷诺数影响试验

Experiment of Reynolds number effects on subsonic compressor plane cascade

采用降低试验压力减小试验叶栅弦长雷诺数的方法,研究了UKG030.3压气机叶型叶片表面和尾迹区域气流随雷诺数、马赫数及攻角变化的流动特性,获得了表面等熵马赫数、总压损失系数等参数随雷诺数的变化规律。试验结果表明:弦长雷诺数减小到一定程度时,叶片吸力面峰值马赫数位置之后会逐渐呈现流动分离气泡产生、分离气泡扩大至分离气泡破碎的过程;长分离气泡出现以后尾迹宽度和叶型总压损失突然急剧增大,但损失突增所对应的临界雷诺数并不一致;叶型总压损失和弦长雷诺数经地面状态参数比值处理以后可以发现,总压损失比突增位置处于0.4倍弦长雷诺数比附近。

The flow characteristics of the UKG030. 3 compressor airfoil surface and the wake area were investigated in details with the varying Reynolds number,Mach number and the angle of incidences by means of decreasing the pressure of the test chamber. The surface isentropic Mach number and the total pressure loss coefficient of the airfoil with the changing Reynolds number were concluded. The experimental results showed that the whole developing process of the separation bubbles,which exhibited appearing,extending and bursting processes,came into sight behind the maximum Mach number location of the airfoil suction side with the test cham-ber pressure and Reynolds number decreasing. When the separation bubbles became long, the width of the wake area and the total pressure loss coefficient increased radically. However, the critical Reynolds number associated with the loss bursting was inconsistent under different conditions. When the total pressure loss coefficient and Reynolds number were divided by the corresponding coefficients of the atmosphere condition, it revealed that the location of the total pressure loss ratio bursting was near 0. 4 times the ratio of the chord Reynolds number.