Corner separation control is studied in this paper on a linear compressor cascade by optimizing the proposed blade end slots. In order to decrease risk of the experiment and obtain a good solution for the end slots considering finite number of calculations, a multi-parameter and multi-objective optimization of the slot to obtain the minimum total pressure loss in the cascade is carried out. Experimental investigation of the optimal slot configuration is conducted and the slot effect on the loss reduction for the compressor cascade has been validated. The slot configuration is optimized at 4° incidence angle to minimize the total pressure loss in the cascade. Measurements are also conducted at 4° incidence angle to validate the optimization procedure and CFD simulations. The layout of the end slot may not be optimal for the whole operating incidence angles for NACA65 cascade, while experiment investigations at 2° and 7° incidence angles with end slot optimized at 4° incidence angle show that total pressure loss is reduced by 5.5% and 23% respectively. The slot configuration can self-adapt the momentum of the jet flow at different incidence angles, due to the change in pressure differential between the pressure and suction surfaces. The blade end slots appear to have significant potential to decrease losses and improve compressor performance and can be applied to the real stator blade to suppress corner separation.

通过优化建议的叶片端槽，在线性压缩机叶栅上研究了角分离控制。为了减少实验的风险并考虑到有限数量的计算来获得端槽的良好解决方案，对槽进行了多参数和多目标优化，以获得级联中的最小总压力损失。进行了最佳缝隙配置的实验研究，并验证了缝隙对降低压缩机级联损失的影响。槽配置在4°入射角处进行了优化，以最大程度地减小级联中的总压力损失。还以4°入射角进行测量，以验证优化程序和CFD模拟。对于NACA65级联的整个工作入射角，端槽的布局可能不是最佳的，而在2°和7°入射角且端槽以4°入射角优化的实验研究表明，总压力损失降低了5.5％和23％。由于压力表面和吸力表面之间的压力差的变化，狭槽构造可以以不同的入射角自适应地调节射流的动量。叶片端槽似乎具有降低损耗和改善压缩机性能的巨大潜力，可以应用于实际的定子叶片以抑制角部分离。分别为5％和23％。由于压力表面和吸力表面之间的压力差的变化，狭槽构造可以以不同的入射角自适应地调节射流的动量。叶片端槽似乎具有降低损耗和改善压缩机性能的巨大潜力，可以应用于实际的定子叶片以抑制角部分离。分别为5％和23％。由于压力表面和吸力表面之间的压力差的变化，狭槽构造可以以不同的入射角自适应地调节射流的动量。叶片端槽似乎具有降低损耗和改善压缩机性能的巨大潜力，可以应用于实际的定子叶片以抑制角部分离。