Numerical Study of the Unsteady Tip Leakage Flow and the Onset of Rotating Stall in a Transonic Compressor

摘要：

Tip clearance flow has significant effect on the rotating stall of axial-flow compressors. In this paper, three-dimensional (3D) single-passage steady/unsteady and multi-passage steady/unsteady numerical simulations of the transonic axial-flow compressor — NASA Rotor 37 had been investigated. The numerical results agree well with the experimental test data as estimation of the global performance. For the single-passage unsteady simulation at near stall condition, detail analyses of the internal flow field with the NASA Rotor 37 led to some preliminary conclusion. The tip leakage flow behaves unsteady obviously. The shock-vortex interaction induces the periodic breakdown of the tip leakage vortex. For near-stall multi-passage unsteady computation, its revealed the unsteady behavior of the tip leakage flow, the interaction of the vortex and the shock wave, triggers the short length-scale — spike type rotating stall inception. Its the forward spillage of the tip leakage flow at leading edge that induces the spike stall inception. As the mass flow ratio decreases, the rotating stall cell is further developed. At the stalled passages, the passage shock is fully detached from the leading edge, and the reverse tip clearance flow is initiated at trailing edge plane. When the rotor is fully stalled, the rotating stall cell is covered almost 4 passages in the blade-to-blade direction, and nearly half of the blade span.

关键词： tip leakage flow unsteadiness stall inception spike spillage.

作者: Yanfeng Zhang Wuli Chu

作者单位: School of Power and Energy,Northwestern Polytechnical University,Xian Shaanxi, China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 184-189

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）