齿轮式燃油泵结构参数多目标多约束优化  

Multi-objective and Multi-constraint Optimization of Structural Parameters of Aviation Fuel Pump

作　　者：柯诗毅 叶志锋[1] 钱一凡 王彬[1] KE Shiyi;YE Zhifeng;QIAN Yifan;WANG Bing(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Institute for Electromagnetic Theory,Hamburg University of Technology,Germany)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]汉堡技术大学电磁理论学院,德国汉堡

出　　处：《机械制造与自动化》2023年第5期144-147,151,共5页Machine Building & Automation

摘　　要：在航空宇航推进领域,提高发动机综合推重比已经成为主要的发展方向。为满足航空发动机主要附件之一的燃油泵流量大、体积小、质量轻的要求,根据齿轮泵的设计需求、零件强度、加工工艺等确定设计约束条件,以体积小、质量轻、流动脉动系数小为优化目标,利用一般遗传算法和非支配排序遗传算法分别进行齿轮泵结构参数的单目标、多目标优化。结果表明:优化后的体积与流量脉动系数都有明显减小。此方法可为齿轮式航空燃油泵的设计提供参考。In the field of aerospace propulsion,improving the comprehensive thrust-to-weight ratio of engines has become the main development direction.In order to meet the requirements of large flow,small volume and light weight of the fuel pump,one of the main accessories of the aero-engine,this paper determines the design constraints according to the design requirements of the gear pump,the strength of the parts,and the processing technology.With large flow,small volume and small flow pulsation coefficency as the optimization objective,the single-objective and multi-objective optimization of the structural parameters of the gear pump were carried out by the general genetic algorithm and the non-dominated sorting genetic algorithm(NSGA-II)respectively.The results show that the optimized volume and flow pulsation coefficency have been reduced significantly,and this method can provide reference for the design of gear type aviation fuel pump.

关 键 词：燃油泵 遗传算法 多约束 多目标优化 

分 类 号：V233.22[航空宇航科学与技术—航空宇航推进理论与工程]