关键词: 平面叶栅；数值模拟；椭圆形前缘；鼓包前缘

Abstract: In order to investigate the effects of plural leading edge modifications simultaneously applied to compressor cascade，a planar compressor cascade which shaped by the blade profile of DMU37 at 5% span was selected as the baseline. A numerical simulation for different leading edge cascade，which included four elliptic leading edges and four elliptic tubercle leading edges，was carried out to investigate the influence on flow field and aerodynamic performance. Length to short axis ratio of ellipse and amplitude of tubercle were considered as the main parameters. Results show that elliptic cascade can variously decrease suction spike and total pressure loss coefficient at incidence of -6° to +4°，especially at positive incidence. A decrease in suction spike of 56.3% and loss coefficient of 5.8% at the incidence of 4° is achieved for elliptic cascade with the best comprehensive properties when its length short axis ratio was four. Elliptic tubercle leading edge cascade shows an increase in loss coefficient at incidence of 0°，however，it effectively decreases loss at incidence of +4°. The highest reduction of total pressure loss coefficient can reach up to 7.5%，which means elliptic tubercle leading edge can improve the aerodynamic performance of cascade.

Key words: Planar cascade；Numerical simulation；Elliptic leading edge；Tubercle leading edge