Optimization of aero-engine combustion chambers with the assistance of Hierarchical-Kriging surrogate model based on POD downscaling method

Advances in Aerodynamics

Research

Wenyan Song¹  Hua Zhang²  Heng Wang²  Jialing Le³  Ye Tian³  Shuhong Tong³  Mingming Guo³  Yue Ma³ 

[1] Northwestern Polytechnical University, 710072, Xi’an, China;Southwest University of Science and Technology, 621000, Mianyang, China;Southwest University of Science and Technology, 621000, Mianyang, China;China Aerodynamics Research and Development Center, 621000, Mianyang, China;

关键词: Aero-engine combustion chamber;    Surrogate model;    POD-Hierarchical-Kriging;    Multi-objective optimization;   

DOI  :  10.1186/s42774-023-00151-3

 received in 2023-02-06, accepted in 2023-04-17,  发布年份 2023

来源: Springer

【 摘 要 】

In view of the long calculation cycle, high processing test and cost of the traditional aero-engine combustion chamber design process, which restricts the engine optimization design cycle, this paper innovatively proposes a surrogate model for the performance of aero-engine combustion chambers based on the POD-Hierarchical-Kriging method. Through experiments, the predicted results of the POD-Hierarchical-Kriging model are compared and analyzed with the calculated results of the one-dimensional program, and the root mean square error of the predicted values of combustion efficiency and total pressure loss is 0.0064% and 0.1995%, respectively. The accuracy of the POD-Hierarchical-Kriging model is compared with the cubic polynomial model, the basic Kriging model and the Hierarchical-Kriging model. It verifies the feasibility and accuracy of the POD-Hierarchical-Kriging model for the prediction of performance of aero-engine combustion chambers. The global sensitivity analysis method is applied to obtain the influence effect of design variables on the performance. Then, a multi-objective optimization method based on the NSGA-II algorithm is studied, and finally the optimal set of Pareto solutions is obtained and analyzed, which can be used to guide the optimal design of aero-engine combustion chambers and accelerate the progress of aero-engine development.

【 授权许可】

CC BY   
© The Author(s) 2023

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