A parametric approach to flow loss with incidence and tip clearance variables for a compressor linear cascade

A study was conducted using theoretical and numerical calculations to analyze the flow losses of a compressor linear cascade called SMU37-RL02. Its main goal is to determine the parametric expressions for vortex structure weight loss at the 103% axial chord position on the quasi-S3 section of the cascade. A flow loss distribution band delineation extraction method is proposed to improve data acquisition efficiency. The method expands the database by single-parameter variable expressions, and the simulated annealing algorithm solves the full-condition optimized tip clearance range for the cascade. The results show that the dominant flow loss weight of the vortex structures is transferred from the passage vortex to the tip leakage vortex following the increased tip clearance. Making the tip clearance C_t = 0.19%H as the optimization objective has the most stable and best performance at the full incoming flow conditions compared to the cascade with an equidistant tip clearance. The maximum loss reduction is 13.16% relative to the original cascade loss at the i = +1.9° incoming flow condition. The optimal cascade achieves relatively stable optimization over the full range of incoming flow conditions.