斜流压气机串列转子流场特性分析

以斜流压气机串列转子为研究对象,运用CFD软件进行了数值模拟,获得了该压气机在100%和80%设计转速下S1流面流场、子午流场、阻塞工况及近失速工况的流场特性,为斜流压气机串列转子的设计和性能分析提供参考。研究结果表明:该斜流压气机在设计转速(69900 r/min)下超声速特性明显,特性曲线较陡峭;当转速小于80%设计转速时亚声速特性明显,特性曲线较平缓。随着转速的减小,压气机的稳定裕度逐渐增大。该斜流压气机串列转子叶根和叶中截面的损失主要来源于叶型尾缘的掺混损失和叶型吸力面的小范围激波损失;而叶尖截面的损失主要来源于叶型吸力面的大范围激波损失、激波与附面层的相互影响的损失和激波与叶尖泄漏流相互作用的损失。该斜流压气机进入近失速工况后,前排转子的激波强度进一步增大,并且叶间存在大范围低速区,造成流动损失进一步增大。

Flow Field Analysis of a Mixed Flow Compressor Tandem-Rotor

Taking tandem-rotor of a mixed flow compressor as an object, flow characteristics of S1 stream surface, meridional channel,blocking point and stall point were obtained by numerical simulations using CFD software to provide reference of design and characteristics analysisof the tandem-rotor. The results show that the mixed flow compressor has obvious supersonic performance and steep performance curve at design speed (69900 r/m). When the speed is lower than 80%design speed, the compressor has obvious subsonic characteristics and a flat characteristic curve. As the speed decreases, the stability margin of the compressor gradually increases. The loss of the tandem-rotor root and middle section is mainly caused by the mixing loss of the blade trailing edge and small shock loss of blade suction; the loss of the tip section is mainly caused by large range shock loss, shock and boundary layer interaction loss, shock and tip clearance vortex interaction loss. After the mixed flow compressor entered near stall point, the shock intensity of the front blade is further enhanced and the tip sectionvisualized a wide low-speed zone, which further increases the flow loss.