进气畸变及非轴对称端壁造型对紧凑型压气机中介机匣性能的影响

To obtain the influence mechanism of non-axisymmetric endwall contouring (NAEC) on the aerodynamic characteristic of a compressor intermediate duct (CID) with large radius change to length ratio under inlet distortion，on the basis of investigating the flow characteristic under inlet distortion，the effects of hub NAEC on the internal flow structure and throttling characteristic of the CID were further explored with numerical method. The results showed that the high total pressure loss and the outlet flow distortion of the CID under inlet distortion were mainly caused by the combined action of the swirl generated by the hub boundary layer separation and the strut corner separation. The proposed NAEC method based on trigonometric function can effectively eliminate the spiral separation nodes on the hub and the strut corner separation，which improved the CID performance significantly，and the total pressure loss coefficient decreased by about 11.4%. In addition， the influence of NAEC on the throttling characteristic of the CID under inlet distortion was different from that of clear inlet condition.