摘要
针对传统超燃冲压发动机燃烧室构型设计中存在的计算周期长、试验成本高等问题,提出一种燃烧室的Kriging代理模型,并使用NSGA-Ⅱ多目标优化算法以实现对超燃冲压发动机燃烧室构型参数高效的优化设计.通过测试,将应用Kriging代理模型的预测结果与CFD计算结果进行对比分析,验证了该代理模型能够较为快速并准确地预测代表燃烧室性能的推力和压力损失系数.以推力和压力损失系数为优化目标,基于NSGA-Ⅱ多目标优化算法,通过该Kriging代理模型获得了Pareto最优解集;然后,采用灵敏度分析法对设计变量进行排序,成功识别出了显著影响燃烧室性能的关键构型参数;最后,基于控制变量法针对单个设计变量的变化对超燃冲压发动机燃烧室性能的影响进行研究,分析结果可以指导燃烧室的优化设计.文章研究结果可加速超燃冲压发动机燃烧室构型的优化设计,为其设计提供了一种新的思路和方法,为后续的相关研究提供了有价值的参考和借鉴.
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.
作者
于江飞
周子旋
彭江鹏
汤涛
杨王锋
杨揖心
汪洪波
Yu Jiangfei;Zhou Zixuan;Peng Jiangpeng;Tang Tao;Yang Wangfeng;Yang Yixin;Wang Hongbo(Hypersonic Technology Laboratory,College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;School of Civil Aviation,Northwestern Polytechnical University,Xi'an 710072,China)
出处
《力学学报》
EI
CAS
CSCD
北大核心
2024年第11期3359-3370,共12页
Chinese Journal of Theoretical and Applied Mechanics
基金
国家自然科学基金资助项目(T2221002和11925207).
