Abstract: To study the flow structure in transonic axial compressor，numerical simulation was conducted with NASA Rotor37 and the flow field parameters were analyzed to explore the vortex flow pattern and structurecoupled with the λ2 criteria. It is found that vortex model in the rotor is consisted of seven major vortexes: horse. shoe vortex，corner vortex，shedding vortex，radial vortex，leakage vortex，induced vortex and separation vortex.Suction side leg of horseshoe vortex is dissipated while pressure side leg develops to adjacent suction side. Majoreffect of shedding vortex and corner vortex induces flow loss and hub corner stall，which are located at the root of blade. Radial vortex，which is located behind shock and in separation zone，enlarges the suction side separationand causes migration of low energy fluid in boundary layer to the tip. Coupling of shockwave and tip leakage in.duces the formation of three vortex structure in blade tip passage，namely leakage vortex，induced vortex and sepa. ration vortex. At outlet of tip cascade，there are two vortexes，separation vortex and tip passage vortex combined by leakage vortex and induced vortex. Blockage in the middle of the flow channel caused by the crushing of leak.age vortex and induced vortex，as well as the low-speed zone caused by separation vortex，trigger instability of transonic axial compressor.

Key words: Transonic axial compressor；Numerical simulation；Vorticity dynamics；Secondary flow；Vortex

摘要： 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。

关键词: 跨声速轴流压气机；数值模拟；涡动力学；二次流；旋涡模型