为研究亚音速高负荷扇形扩压叶栅NACA0065-K48的变工况性能，采用数值方法研究了来流马赫数对叶栅气动性能和流场结构的影响，来流马赫数的取值范围为0.3~0.8。计算结果表明：随着来流马赫数的增大，叶栅静压比不断提高，但总压损失先减后增，马赫数在0.5~0.7范围内叶栅具有较好的综合气动性能。扇形叶栅下角区分离程度大于上角区的不平衡流动现象会随着马赫数的增大而加剧，通道涡则是这一发展趋势的主导，且马赫数达到0.7之后，下角区通道涡与集中脱落涡趋于融合。此外，下端壁分离螺旋点的形成与发展是控制下角区分离程度和损失大小的关键。

To explore the performance of a subsonic highlyloaded sectorial compressor cascade NACA0065K48 under variable working conditions,the influence of incoming Mach number on aerodynamic performance and flow field structure is studied by numerical simulation.The value range of the incoming Mach number is 0.3 to 0.8.The computing results show that,with the increase of Mach number,the static pressure ratio of the cascade increases,but the total pressure loss decreases first and then increases.The cascade has better overall aerodynamic performance when Mach number is in the range of 0.5 to 0.7.The separation in the lower corner of sectorial cascades is more serious than the upper corner.This unbalanced flow appearance will aggravate with the increase of Mach number,and the passage vortex is actually the primary cause.The passage vortex in the lower corner tends to merge with the concentrated shedding vortex when the Mach number is greater than 0.7.In addition,the formation and development of the separation helix on lower endwall is the key to control the corner separation and the loss.

V231.3

上海市部分院校能力建设专项计划（16060502600）