转子尖部角区分离对高负荷压气机性能影响的实验与数值研究

In order to investigate the effects of rotor tip corner separation on the performance and the internal flow field of high-load compressors， a single-stage high-load compressor， with the 0.46 loading coefficient， have been designed. Compressor stage characteristics and internal flow fields were studied by experiments and numerical simulations under two rotor tip clearance conditions， i.e. 0.6% and 1.3% blade span. The variation of characteristics and its flow mechanisms have been analyzed. The results show that， when the rotor tip clearance is 0.6% blade span， a significant corner separation occurs on the suction side at the rotor near-casing region under the near-stall conditions， while the tip leakage flow is predominant when the rotor tip clearance is 1.3% blade span. With the enhancement of the corner separation， the local blockage and loss increase dramatically. Meanwhile， due to the enhanced radial migration flow on the rotor suction surface， the loss decreases and the loading level increases in the rotor near-hub region under the near-stall conditions. Correspondingly， the total pressure rise of the compressor under the near-stall conditions exhibits a characteristic trend of initially slow variation， then increasing， and finally rapidly decreasing as the flow rate decreases， with the stage efficiency rapidly decreases as the total pressure rise further increases under the near-stall conditions.