To alleviate the adverse effects of the flow-field structure caused by interstage sealing structures on the aerodynamic characteristics of compressor cascades, a blade-root through-slot structure was designed in this study. The structure links the pressure surface to the suction surface of the blade. Numerical simulation techniques were utilized to investigate the process. In this process, the through-slot structure enhances corner separation across varying jet positions, jet heights, and jet widths. The results indicate that the high-speed fluid ejected by the through-slot configuration can suppress the accumulation of low-energy fluid at the suction root. It can also alleviate blockages in the cascade passage and reduce the range of separation vortices and recirculation zones on the suction side. Consequently, the flow loss due to separation is reduced. As the through-slot jet progresses from the blade leading edge to the trailing edge, its restraining impact on the low-energy fluid cluster gradually diminishes. This leads to a corresponding reduction in its effect on the total pressure loss. With an increase in the slot height, the restraining impact on corner separation and total pressure loss first rises and then falls. As the through-slot height increases, the suppressive effect on corner separation and loss initially intensifies and then weakens. As the through-slot width increases, the suppressive effect on corner separation and total pressure loss increases steadily. Compared to the original compressor cascade, the through-slot configuration attains peak performance at 25% chord length, with a height of 6% height and a width of 10 mm, reducing the total pressure loss coefficient by 19.22%. Furthermore, as the incoming flow incidence angle enlarges, the enhancement impact of the through-slot configuration on cascade performance initially intensifies and then diminishes. The peak enhancement impact occurs at a 0° incidence angle. At this angle, the configuration can reduce flow loss by 16.72% compared to the original, significantly improving the aerodynamic performance of the high-load compressor cascade.

With the advancement of aeroengines toward higher pressure and efficiency, the advantages and disadvantages of the compressor working environment significantly affect the whole machine’s performance. Boundary layer separation deteriorates the flow field structure. End-wall suction technology is an end-zone control technology that can enhance the aerodynamic performance and flow field structure. This study numerically simulated the influence of end-wall suction at different positions on the vortex evolution and aerodynamic performance under various working conditions. The results suggest that end-wall suction can effectively improve the flow field, reduce the corner separation region, and inhibit low-energy fluid cluster aggregation, thereby improving the cascade diffusion capacity and reducing flow loss. The suction effect gradually diminishes as the suction position moves closer to the trailing edge (TE). The total pressure loss is reduced by 16% when implementing suction at the leading edge (LE), and the loss reduction effect is the best. Furthermore, the suction effect shows a trend of increasing initially before diminishing as the incidence angle increases. When the incidence angle is 0°, the suction effect is the most potent.