Design Optimization of 1.5-Stage Transonic Compressor Based on BPNN Surrogate Model and NSGA-II

To achieve multi-objective aerodynamics design optimization for a 1.5-stage transonic compressor, platform incorporating blade parameterization methods, BPNN surrogate model, and the NSGA-II method was developed. The stagger angle distribution of three rows selected as variable, with isentropic efficiency at new condition stall margin set goal functions. Results demonstrated that, without altering profile shape endwall contour, flow rate increased by 7.1%, 1.8%, decreased 0.0087, total pressure ratio experienced slight increase. field different conditions before after compared analyzed. analysis indicated that tangential velocity rotor outlet becomes determining factor compressor’s work capacity. relative Mach number inlet emerged key parameter affecting shock wave intensity wave/boundary layer interaction, which directly influenced passage. At near condition, stator vane root’s is crucial performance.