Comparison of NPU and DLR design of axial-flow compressor rotor cascade

The method of optimization design for the transonic axial flow compressor cascade was proposed. The conditions of aerodynamic design for the rotor cascade with inlet Mach number 0.918 were provided by DFVLR. The experimental results of aerodynamic performance for the cascades, designed respectively by Northwestern Polytechnical Univ (NPU) and DFVLR, in two dimensional cascade wind tunnel were compared. It has been shown that both cascades are of satisfactory global performance, the operating range of low incidence is wider for NPU cascade, but the minimum total pressure loss is lower for DFVLR cascade. Due to effective control for thickness distribution of the blade, the proposed method is more practical.