Aerodynamic Optimization and Mechanism Investigation on Performance Improvements in a Transonic Compressor Cascade

In this paper, a transonic compressor cascade was optimized to improve its aerodynamic performance. A new blade parameterization method with 16 control variables first proposed fit the shapes of suction and pressure side, as well leading edge. Then, Kriging surrogate-model-based genetic algorithm (GA) used optimize performance cascade. The optimization is effective in reducing total loss while extending working range results show that coefficient could be reduced by 11% at best airflow angle extended 6.9% for two-dimensional simulations. Similar improvement also obtained simulations their linear cases. Detailed analyses relative maximum thickness positions blades move forward about 10% edge, radii curvature front half surfaces increase, compared initial blade. This makes look more closely like wedge. Consequently, passage shock strength changes from normal oblique shock. weakened leads disappearance flow separation caused boundary layer interaction on blades, narrowed wake width outlet section.