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设计了7组不同轴向间隙的对转压气机几何数据,应用数值模拟手段获取其性能和流场细微结构,研究了对转转子轴向间距对压气机性能、进气角以及流场结构的影响.结果表明:①在轴向间隙从30%C(C为转子叶片根部弦长)到70%C增加的过程中,对转压气机峰值效率降低2%左右,上、下游对转转子峰值效率也降低约4%;②设计转速下近失速点效率和流量先上升后降低,在55%C间距时达到最大值;堵塞点流量增加,效率降低约3%;③在堵塞工况下,随着轴向间隙的增加上、下游转子进口气流角减小;④当轴向间隙增大至50%C时,继续增大对上下游转子来流攻角影响不大;⑤如果掺混损失占主导地位,通过减小轴向间距可有效提高压气机性能,如果是二次流损失占主导地位通过增加轴向间距来提高压气机性能是可行的方法.
Seven sets of geometrical data of counter-rotating compressor with different axial clearances were designed. The performance and flow field microstructure of the compressor were obtained by numerical simulation. The influences of rotor axial distance on compressor performance, inlet angle and flow field structure The results show that: (1) when the axial clearance increases from 30% C (C is the root chord length of the rotor blade) to 70% C, the peak efficiency of the turbo compressor is reduced by about 2% The peak efficiency is also reduced by about 4%; (2) the efficiency and flow rate at the stall point at the design speed first increase and then decrease, reach the maximum at the 55% C spacing; the traffic at the clogging point increases and the efficiency decreases by about 3%; , As the axial clearance increases, the inlet airflow angle of the downstream rotor decreases; ④ When the axial clearance is increased to 50% C, the effect of continuing to increase the angle of attack on the upstream and downstream rotors is not significant; Mixing loss dominates. Compressor performance can be effectively increased by reducing axial spacing. If the loss of secondary flow dominates, it is viable to increase the performance of the compressor by increasing axial spacing.