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本文以NASA rotor 35为研究对象,采用定常和非定常数值模拟方法对其全稳定工况范围内的流场进行了数值模拟.以此为基础,将广泛应用于旋涡结构识别的特征向量法和Lambda 2方法引入到压气机叶尖流场的分析中.流场分析表明:当在流向涡稳定发展时,lambda 2方法和特征向量法均可以准确地提取叶尖流场中的主要涡旋;当流向涡结构遭到破坏时,lambda 2方法在涡破碎区失效,而特征向量法则可以更为深入地描述破碎区的情况.从阻塞工况到近峰值效率工况,叶尖通道中除了主间隙涡之外还有若干二次间隙涡,二次间隙涡的分布与通道中激波的变化紧密相关;而从近峰值效率工况到失速边界工况,叶尖涡系不再发生变化,但主间隙涡与激波干涉效应不断增强,叶尖流场先后历经了激波后近压力面侧低速阻塞区的出现、主间隙涡的泡式及螺旋式破碎.“,”In this paper,the flow field over the full stable operating range in a transonic axial flow compresor rotor,NASA Rotor 35,are investigated by steady and unsteady simulations.Based on the simulation results,the flow field near the rotor tip are analyzed in detail by introducing the lambda 2 and the eigenvector methods,which are widely used to extract the votrex structures.The results show that if vortices develops stably,both methods can extract the main vortex structures in the rotor tip region accurately.However,if the bursting of vortices occurs,the lambda 2 method becomes invalidated while the eigenvector method can still be used to describe the flow field in the breakdown region deeply.From the choked flow condition to the near peak efficiency flow condition,the primary clearance vortex is dominant,but there are several secondary clearance vortices,which number and locations depond on the variation of the shock waves versus back pressure.From the near peak efficiency flow condition to the near stall flow condition,the number and locations of tip vortices are no longer varied due to the disappearance of the second shock wave.However,the interaction of the primary clearance vortex and the shock wave becomes stronger and stronger with the back pressure increased.This leads to three milestones in flow variation,which are depicted in sequence as an appearance of a low-veloctiy area behind the shock wave and near the pressure side of the passage,the bubble-type breakdown of primary clearance vortex and the sprial-type breakdown of primary clearance vortex.