In order to explore the influence of cavity leakage flow on the aerodynamic performance and flow field structure of the annular diffuser cascade,the annular diffuser cascade was studied based on the verified numerical simulation meth-od,and the effects of leakage flow rate and circumferential ve-locity on corner separation and total pressure loss were ana-lyzed. Results show that as the leakage flow increases,the ex-pansion range of the passage vortex (PV) becomes larger,the corner separation occurs earlier,and the total pressure loss coefficient of the blade gradually increases. When the leakage flow coefficient increases to 1.5％,the total pressure loss co-efficient expands by 22. 9％. The increase in circumferential velocity of the leakage flow improves the blockage situation in the near end wall area. The degree of deviation of the fluid close to the end wall towards the suction surface is weakened,and the range of deviation is reduced. When the circumferen-tial velocity coefficient increases to 1.1,the total pressure loss coefficient decreases by 21.3％.
关键词
压气机/容腔泄漏流/环形扩压叶栅/气动性能/数值模拟
Key words
compressor/leakage flow in the containment chamber/annular diffuser cascade/aerodynamic performance/numerical simulation
维普
万方数据