压气机角区失速预测模型的改进与实验验证

Endwall corner separation is a typical secondary flow in axial compressor. With the increase of blade loading, the corner separation flow could develop into corner stall flow, which could cause serious flow blockage and loss in compressor blade passage and should be avoided during the compressor design procedure. In order to predict the corner stall flow in compressors, some criterions has been developed, which are mainly based on two-dimensional airfoil data. The endwall flow is strong three-dimensional in real compressor environment. A new criterion is developed accordingly in the present paper. The newly developed criterion was verified by experimental data obtained from low-speed compressor tests. The results showed that the existed criterions do not work well in real compressor environment and the newly developed criterion could accurately predict the stator hub corner stall in compressors with a critical value of D=0.405±0.02. In addition, the newly developed D parameter shows related correlation to the flow loss and blockage in compressor stators.