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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 single-stage axial compressor as the research object, the aerodynamic parameters of the interstage and outlet were measured by pneumatic probe, and the full three-dimensional numerical simulation of the internal flow field in the stator with / without clearance was performed. The calculated radial distribution of compressor’s performance, interstage and outlet parameters is consistent with the experimental results. On this basis, the complicated flow structure of the stator end region with / without sharp-edge was analyzed comparatively. It is found that the stall in the corner region of the hub / suction face is the main flow characteristic of the stator end region of the compressor. In the absence of a sharp gap, the space around the hub / suction corner is surrounded by a ring-shaped vortex structure formed by the convergence of multiple vortices and inducing a large amount of backflow on the suction side. The introduction of a sharp gap breaks the ring vortex Structure, but it forms a leakage vortex along the flow direction in the hub / suction corner region and enhances the strength of the radial separation vortex at the outlet of the passageway, thus increasing the total pressure below 30% leaf height at near stall conditions The area of loss.