Research on the effect of channel parameter on the aerodynamic design and performance of two-dimensional high-subsonic compressor cascade

The design of two-dimensional axial compressor cascades is essential to the development of high-performance aero engines; however, there remains no unified guideline for aerodynamic design. In this study, it employed a blade modeling method, introducing the concepts of load distribution coefficient and equivalent channel diffusion angle, which allowed the construction of two-dimensional cascades with varying load distribution coefficients, camber angle, and solidity. Subsequently, validated numerical computation methods were applied to determine the optimal load distribution coefficient for different cascades. The corresponding minimum total pressure loss coefficient was found to present a ring-shaped distribution pattern around the origin position of the cascade camber angle and solidity plane coordinate system. In addition, a linear trend was observed in the values of the equivalent channel diffusion angle. Based on that, a comparative analysis was conducted on the performance and flow field of cascades with the same equivalent channel diffusion angle under different inflow Mach numbers. It revealed a common feature in flow behavior and underlying mechanisms, thereby confirming the importance of channel parameters in blade design. Nevertheless, substantial differences in camber angle and solidity were found to reduce these flow commonalities. Factors, such as greater variation of the channel diffusion angle in the front section of the cascade, forward shifts in load distribution, and larger camber angles predominantly affected boundary layer development. These effects led to a rapid increase in the boundary layer relative displacement thickness, which in turn weakened or even eliminated the influence of high solidity in suppressing boundary layer separation.