跨声速轴流压气机近失速状态的间隙泄漏流流动特性

为了研究间隙泄漏流以及泄漏涡自身的非定常性对轴流压气机的旋转失速的影响.对跨声速轴流压气机NASA转子37进行全三维定常、非定常的数值模拟,对比了最大效率和近失速工况的实验和数值模拟结果,定常计算所获得的总性能与试验结果符合良好.对于非定常计算,详细分析了NASA转子37近失速工况下流场结果,揭示了NASA转子37在近失速工况点,间隙泄漏流存在较明显的非定常性,这种非定常性表现为间隙泄漏流激波干涉引起间隙泄漏涡的周期性破碎.

Numerical simulation of the flow characteristic of tip leakage flow in a transonic axial-flow compressor at near stall condition

Tip clearance flow and the unsteady flow phenomena of tip leakage vortex have great effect to the stall inception of axial-flow compressor.In this paper,3-D steady,unsteady numerical simulation of the transonic axial-flow compressor-NASA rotor 37 was investigated.Compared to the numerical results and the experimental test case at peak-efficiency and near stall condition,the numerical results agreed well with experimental test data for estimation of the global performance.For the unsteady computation,Detail analyses of the flow field of the NASA rotor 37 led to some preliminary conclusion: the tip leakage flow behave obviously unsteady flow phenomena.Shock-vortex induced the periodic breakdown of the tip leakage vortex.