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根据栅前至栅后１２个横截面内的气动参数和沿叶高９个叶型的静压系数测量结果，分析了气流绕流叶栅损失增长的根源。实验结果证明：（１）在叶栅进口端壁附面层分离，形成复杂进口涡系；（２）在叶栅出口在径向压力梯度的作用下，主流、尾流、集中涡系和新生附面层相互掺混；是气流绕流叶栅损失增长的两个根源。
According to the aerodynamic parameters in the 12 cross sections between the front of the grid and the gate and the static pressure coefficient of 9 blades along the height of the blade, the root causes of the increase of the flow around the flow cascade are analyzed. The experimental results show that: (1) At the cascade inlet of the cascade inlet, the complex inlet vortex system is separated; (2) Under the radial pressure gradient at the exit of cascade, the main stream, wakes, Blending of the facing layers is the two root causes of the loss of air flow around the flow cascade.