A Supersonic Compressor Cascade Aerodynamic Design and Optimization Methodology with Curvature Control

Addressing the issue of boundary layer separation and flow instability caused by shock wave–boundary layer interaction in supersonic compressor cascades, this work presents a novel aerodynamic design and optimization method for supersonic cascades. This method is based on a design philosophy of enhancing control over the shock wave and boundary layer by employing a blade channel with a curvature-continuous profile. An aerodynamic redesign and optimization methodology was conducted on the ARL-SL19 supersonic cascade, aiming to improve its aerodynamic performance and widen the stable operating range. The results indicate that for a low-loss diffusing channel, the design principle for the suction surface profile involves controlling the shock strength via the curvature of the forward section, while the aft section should feature a smooth and negative curvature variation. This approach facilitates the control of the boundary layer flow, thereby improving the overall aerodynamic performance of the supersonic cascade. Compared to the baseline, the aerodynamically optimized cascade demonstrates a 10.74% reduction in the total pressure loss coefficient at the design point. Furthermore, its performance at off-design conditions is also significantly enhanced: the near-stall total pressure loss coefficient is reduced by 6.66%, the maximum total pressure ratio is increased by 6.32%, and the stable operating range with low flow loss is considerably extended.