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本文采用组合多项式曲线构造了具有高亚音进口条件的大折转角压气机静叶叶型,探索了进一步提高跨音速压气机负荷时,静叶根部区域可能存在的激波结构和损失特征。采用数值模拟方法对不同条件下的高亚音速大折转角压气机叶栅流场进行了数值模拟,结果表明:叶栅内的激波结构与进口马赫数、攻角以及叶型的转角等参数密切相关。通过对叶栅出口的损失分析发现,激波与附面层相互作用改变了原有附面层内的损失分布规律,形成了由激波强度和位置所决定的沿叶片表面法线方向大小基本不变的高损失区域,叶型损失的大小和激波与吸力面最低压力点之间的相对位置密切相关。
In this paper, a combinatorial polynomial curve is used to construct a large-angle compressor turbo leaf with high subsonic inlet conditions. The possible shock structure and loss characteristics in the root region of the static impeller are explored when the transonic compressor load is further increased. Numerical simulations were carried out to simulate the cascades flow field under different conditions with high subsonic large deflection. The results show that the shock wave structure, Mach number of entrance, angle of attack and the angle of rotation of the blade closely related. Through the analysis of the loss of cascade exit, it is found that the interaction between the shock wave and the coating changes the distribution of the loss in the original coating, and forms the basic size of the surface normal to the blade surface determined by the intensity and position of the shock The invariable high-loss area is closely related to the size of the loss of the vane and the relative position of the shock and the lowest pressure point on the suction side.