Abstract: The effects of boundary layer suction on the aerodynamic performance of low-speed compressor cascade with highly loading are numerically studied. The baseline compressor is considered to perform a numerical investigation and by comparing with the experimental data available from literature, the reliability of commercial computational fluid dynamics(CFD) computational code is validated. The results show that computed performance maps achieve a good agreement with the experimental data, so it’s practicable by using the means of numerical simulations on the study. The distributions of exit total pressure loss at different positive incidences are analyzed, and the limited streamline at suction surface and end wall also are given. The results show that boundary layer suction improves effectively the aerodynamic performance of compressor cascade, and the flow separation at the corner will be restrained for low-energy flow aspirated, which results in the decrease of total pressure loss at exit. As incidence increases, greater performances improvement can’t be achieved by a smaller suction rate, unless the suction flow rate is increased. At +10° incidence, the flow control ability is weaken for the strong separation condition by boundary layer suction, and the aerodynamic performance in compressor is even worse at a smaller suction rate.

Key words: Aspirated compressor, Boundary layer suction, Flow separation, Numerical investigation