马赫数分布可控轴对称进气道多目标优化设计  

Mach number distribution controllable axisymmetric inlet multi-objective optimization design

作　　者：田新辉 李永洲 袁熠祺 杨学良 孙迪 TIAN Xinhui;LI Yongzhou;YUAN Yiqi;YANG Xueliang;SUN Di(College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《兵器装备工程学报》2024年第11期212-221,共10页Journal of Ordnance Equipment Engineering

基　　金：江西省研究生创新专项基金项目(YC2022-s373);江西省“双千计划”创新领军人才项目;航空发动机热环境和热结构工信部重点实验室开放基金项目(CEPE2022005);航空科学基金项目(20240012056001)。

摘　　要：针对马赫数分布可控的曲面压缩轴对称进气道,对外压段和内压段所有设计参数进行灵敏度分析,获得了设计参数对进气道性能和几何参数的影响规律,其中前缘半锥角δc对进气道长度L的影响最大且为负效应,系数b和c以及唇口内角ω对性能参数影响较为明显。在此基础上建立代理模型进行三目标优化,得到了综合性能较优的轴对称进气道。与基准进气道相比,优化进气道在长度缩短11.2%的基础上,在整个工作范围内具有更高的压缩效率和低马赫数流量捕获能力。Ma4.0~7.0范围内喉道总压恢复系数最大提升19.2%,Ma4.0时流量系数相对提升了6.54%。Based on the sensitivity analysis of all design parameters of the curved compression axisymmetric inlet with controllable Mach number distribution,the influence of design parameters on the inlet performance and geometric parameters is obtained.The influence of the leading edge half-cone Angleδc on the inlet length L is the largest and negative effect,and the coefficients b and c and the inside Angle of the lip have a more obvious influence on the performance parameters.On this basis,a proxy model is established for three-objective optimization,and an axisymmetric inlet with better overall performance is obtained.Compared to the benchmark inlet,the optimized inlet has higher compression efficiency and low Mach number flow capture over the entire operating range with an 11.2%reduction in length.In the range of Ma 4.0-7.0,the total pressure recovery coefficient of the throat increased by 19.2%at the maximum,and the flow coefficient increased by 6.54%at Ma 4.0.

关 键 词：轴对称进气道 马赫数分布规律 弯曲激波 灵敏度分析 优化设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]