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为了明确跨声速轴流压气机内部流场结构,数值模拟了NASA Rotor37转子,结合λ2准则分析流场参数,探索流动的规律和旋涡结构。研究发现,压气机转子的旋涡模型主要由马蹄涡、壁角涡、径向涡、脱落涡、泄漏涡、诱导涡和分离涡等7个旋涡组成。马蹄涡吸力面分支耗散,压力面分支向相邻的吸力面发展。壁角涡与脱落涡位于叶根角区,引起流动损失和角区失速。径向涡位于激波后吸力面的分离区内,它扩大吸力面分离、引起低能流体向叶顶堆积。激波与叶尖泄漏在叶顶通道中形成3涡:泄漏涡、诱导涡和分离涡,而叶栅通道出口存在分离涡和由泄漏涡与诱导涡合成的叶顶通道涡。泄漏涡与诱导涡破碎在流道中间产生的堵塞区,分离涡造成吸力面尾缘的低速区,共同触发跨声速压气机的失稳。
In order to clarify the flow field structure of the transonic axial flow compressor, the NASA Rotor37 rotor is numerically simulated. The flow field parameters are analyzed based on the λ2 criterion, and the flow law and the vortex structure are explored. It is found that the vortex model of compressor rotor mainly consists of seven vortices such as horseshoe vortex, corner vortex, radial vortex, shedding vortex, leakage vortex, induced vortex and separation vortex. Horseshoe vortex suction surface branch dissipation, pressure surface branch to the adjacent suction surface development. Corner vortices and shedding vortices are located in the root zone of the root, causing loss of flow and stalling of the corner zone. The radial vortices are located in the separation area of the suction surface after the shock wave, which enlarges the separation of the suction surface and causes the accumulation of low-energy fluid toward the top of the blade. Shock and tip leakage form three vortices in the tip-top channel: leaking vortex, induced vortex and separation vortex, while there are separate vortex at the exit of cascade and tip vortex channel formed by leakage vortex and induced vortex. Leakage vortex and induced vortex crushing generated in the middle of the flow channel blockage, separation vortex caused by the suction surface trailing edge of the low-speed zone, jointly trigger transonic compressor instability.