OPTIMIZATION DESIGN OF COMBUSTION CHAMBER CONFIGURATION PARAMETERS FOR SCRAMJET ENGINES BASED ON SURROGATE MODELS

This article aims to address the problems of long calculation cycles and high experimental costs in the design of traditional scramjet engine combustion chamber configurations. A Kriging surrogate model for the combustion chamber is proposed, and the NSGA-II multi-objective optimization algorithm is used to achieve efficient optimization design of combustion chamber configuration parameters for scramjet engines. Through tests, the prediction results of the Kriging surrogate model were compared and analyzed with the CFD calculation results, verifying that the surrogate model can quickly and accurately predict the thrust and pressure loss coefficients representing combustion chamber performance. Based on the NSGA-II multi-objective optimization algorithm, the Pareto optimal solution set was obtained using the Kriging surrogate model with thrust and pressure loss coefficients as optimization objectives. This article also conducted sensitivity analysis to rank design variables and successfully identified key configuration parameters that significantly affect combustion chamber performance. In addition, this article also conducts research on the impact of changes in a single design variable on the performance of a scramjet engine combustion chamber based on the control variable method, and the analysis results guide the optimization design of the combustion chamber. Based on these research results, the optimization design of the scramjet engine combustion chamber has been accelerated, providing a new approach for the design of the scramjet engine combustion chamber, and providing valuable reference and inspiration for subsequent related research.