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为探明附面层抽吸技术对压气机叶栅气动性能的影响及其与栅内旋涡结构的关联,通过十个横截面的实验测量结果研究了高负荷压气机叶栅抽吸端壁附面层前后的主要旋涡结构以其对应损失的演变过程。研究对象为矩形低速扩压叶栅,来流马赫数约为0.23。研究结果表明,端壁附面层的变化对叶栅端区的主要旋涡发展过程影响显著。在原型方案中,壁面涡、尾缘脱落涡的演变过程对应着较高的流动损失,通道涡自身产生的损失较小,主要起到向远离端壁的方向输运低能流体的作用;在流向槽吸气方案中,壁面涡和尾缘脱落涡因端壁附面层径向迁移及角区分离受到抑制而被明显削弱;而来流附面层抽吸方案则最为有效地控制了通道涡的演变过程。
In order to find out the influence of top layer suction technology on the aerodynamic performance of compressor cascade and its correlation with the vortex structure in the grid, the experimental results of 10 cross-sections were used to study the effect of suction on the end wall of compressor cascade The main vortex structure before and after the surface layer of its corresponding loss of evolution. The research object is a rectangular low-speed compressor cascade, Mach Mach number is about 0.23. The results show that the change of the top coat has significant influence on the development of the main vortex in the end region of the cascade. In the prototype scheme, the evolution of wall eddy and trailing edge shedding vortex corresponds to high flow loss, and the loss of channel vortex itself is small, which mainly plays the role of transporting low-energy fluid away from the end wall. In the flow direction In the slot suction scheme, the vortex shedding on the wall vortex and tailing vortex were significantly weakened due to the radial migration of the overburden on the endwall and the suppression of the separation of the corner regions. However, The evolution of the process.