静子轮毂角区失速与尖隙流动相互作用机理分析  

The Analysis of Interactional Mechanism Between Hub Corner Stall and Tip Leakage Flow in an Axial-Flow Compressor Stator

作　　者：田江涛[1] 吴艳辉[1] 李清鹏[1] 楚武利[1] 张皓光[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《工程热物理学报》2011年第12期2034-2039,共6页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51076133);航空科技创新基金资助项目(No.08B53004);航空科学基金资助项目(No.2010ZB53016)

摘　　要：以某单级轴流压气机为研究对象,采用气动探针对其级间及出口气动参数进行了测量,并对叶顶有/无间隙时的静子内部流场进行了全三维数值模拟。计算得到的带尖隙时压气机总性能、级间及出口参数的径向分布与实验结果较为一致。在此基础上,对比分析了有/无尖隙时静子端区的复杂流动结构,发现轮毂/吸力面角区失速是该压气机静子端区的主要流动特征。无尖隙情况下,在轮毂/吸力面角区仔在一个由多涡系汇聚而成的空间环涡结构,并在吸力面诱导出大量反流;而尖隙的引入破环了该环涡结构的形成,但它在轮毂/吸力面角区形成了沿流向发展的泄漏涡、增强了通道出口径向分离涡的强度,从而增大了近失速工况点30%叶高以下高总压损失区的范围。Taking a certain single-stage axial-flow compressor as the subject investigated, the interstage and outlet aerodynamic parameters were measured with pneumatic probes. Moreover, full three-dimensional numerical simulations were carried out to investigate the internal flow field of the stator with and without tip clearance. The overall performance and the spanwise distribution of tile interstage and outlet parameters with tip clearance were predicted, and the results agreed well with the experimental data. The flow field near the endwall with tip clearance was compared with that without tip clearance, and it was found that the hub-suction surface corner stall was the main flow characteristic near the endwall. In the case without tip clearance, there existed a ring-like vortex structure near the hub-suction surface corner region, which consisted of multi-vortex system, and the vortex could induce a large amount of overturning flow on the suction surface. The introduction of tip clearance destroyed the formation of ring-like vortex structure, however a streamwise leakage vortex were formed at the hub-suction surface corner region. Meanwhile, the intensity of the spanwise separation vortex at the outlet of the passage was greatly increased. Both the leakage vortex and the increased separation vortex at the outlet edge enlarged the range of high total pressure loss under the 30% span at near stall condition.

关 键 词：静子 角区失速 尖隙泄流 环涡 反流 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]