高马赫数低雷诺数的涡轮叶栅试验  

Experiment of turbine cascade under high Mach number and low Reynolds number conditions

作　　者：段文华[1] 陈伟杰[1] 赵鑫雨 乔渭阳[1] DUAN Wenhua;CHEN Weijie;ZHAO Xinyu;QIAO Weiyang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129

出　　处：《航空动力学报》2024年第10期418-427,共10页Journal of Aerospace Power

基　　金：国家民机预研项目(MJ-2017-D-32);国家重大科技专项(2017-Ⅱ-0008-0022);国家自然科学基金青年项目(52106056)。

摘　　要：以高速低压涡轮叶型为研究对象,在高马赫数低雷诺数条件下,对叶栅损失进行了平面叶栅试验研究和数值模拟研究。试验研究了等熵出口马赫数范围0.66~1.23,雷诺数范围1.1×10^(5)~9.0×10^(5)条件下平面叶栅损失特性,并对典型工况下的流场进行了数值模拟。重点分析了高亚声速条件下雷诺数对叶栅性能的影响及跨声速条件下不同雷诺数条件下激波对边界层流动的影响。结果表明:在高亚声速条件下,随着雷诺数的降低,吸力面从无分离逐步发展为闭式分离泡,最终开式分离;层流分离的起始位置受等熵出口马赫数影响不大,出口马赫数影响分离边界层的转捩和再附。跨声速条件下叶片吸力面将会发生激波层流边界层干涉,干涉后的边界层流动取决于雷诺数大小和激波的强度。数值模拟的结果与试验结果一致性良好,但在极低雷诺数条件下对压力系数的预测存在数值上的差异。A high speed low pressure turbine cascade was experimentally and numerically studied under high Mach number and low Reynolds number conditions.The loss characteristics of cascade under isentropic outlet Mach number range of 0.66—1.23 and Reynolds number range of 1.1×10^(5)—9.0×10^(5) were studied experimentally,and the flow field under typical conditions was simulated.The influence of Reynolds number on cascade performance under high subsonic speed conditions and the influence of shock wave on boundary layer flow under different Reynolds number conditions were mainly analyzed.The results showed that when the Reynolds number decreased under high subsonic speed conditions,the suction side boundary layer developed from no separation to a closed separation bubble,and finally to an open separation.In the absence of shock wave,the starting position of laminar separation was not greatly affected by isentropic outlet Mach number,which mainly affected the transition and reattachment position of the separation boundary layer.Shock laminar boundary layer interactions occurred on the suction surface of the blade under transonic conditions.The development of the boundary layer after interaction relied on the Reynold number and the strength of shock.The numerical results were in good agreement with the experimental results,but there were differences in the prediction of the pressure coefficient at very low Reynolds numbers.

关 键 词：高马赫数 低雷诺数 低压涡轮 平面叶栅试验 边界层 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]