超声速风洞喷管冷却结构的多目标优化设计  

Multi-objective optimization design of supersonic wind-tunnel nozzle cooling structure

作　　者：杨洪涛 游广飞 徐亮[2] 阮麒成 YANG Hongtao;YOU Guangfei;XU Liang;RUAN Qicheng(Zhengzhou Research Institute of Mechanical Engineering Company,Limited,Zhengzhou 450052,China;State Key Laboratory for Manufacturing Systems Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]郑州机械研究所有限公司,郑州450052 [2]西安交通大学机械制造系统工程国家重点实验室,西安710049

出　　处：《航空动力学报》2023年第5期1047-1057,共11页Journal of Aerospace Power

基　　金：国家自然科学基金(51876157);陕西省自然科学基金(2019JM-096)。

摘　　要：针对某风洞喷管提出了一种水冷结构,即在喷管前后段壁内设置了24组流道,而在喉部区域壁内错排布置扰流柱阵列。采用气热耦合-结构热分析的数值模拟方法对喷管整体结构的流动、换热、刚度性能进行了计算和分析。计算结果表明:冷却水量为1 kg/s时,与基础件相比,提出的冷却结构的概念件平均冷却效率提升0.68%,喉部等效应变减小5%左右。采用了响应面模型近似方法和多岛遗传算法对概念件进行了多目标优化计算,结果表明:冷却水量为2.142 9 kg/s时,与概念件对比,优化件壁面最高温度可以降低1.6 K左右,喉部等效应变减小约10%。喷管冷却结构设计及其多目标优化方法为风洞喷管型面有效的热防护设计提供一定的参考。A cooling structure for nozzle of a wind tunnel was proposed,that is:24 channels were set on walls of anterior and posterior segments of the nozzle while staggered pin-fin structure was set on wall of nozzle throat area.The numerical simulation method of the conjugated heat transfer-structural thermal analysis was used to calculate and analyze the fluid flow,heat transfer,and stiffness performances of the overall nozzle structure.The calculation results showed that under the cooling water mass flow rate of 1 kg/s,the averaged cooling efficiency of the proposed cooling structure of the conceptual nozzle was 0.68%higher than that of the basic structure,and equivalent elastic strain of throat area of the nozzle was reduced by around 5%.The response surface model approximation method and multi island genetic algorithm were used to perform multi-objective optimization calculation of the conceptual nozzle.The results showed that the maximum wall temperature of the optimized structure was about 1.6 K lower than that of the conceptual one under the cooling water mass flow rate of 2.1429 kg/s,and equivalent elastic strain of throat area of the nozzle was reduced by around 10%.The cooling structure design of the nozzle and its multi-objective optimization method may provide a reference for an effective thermal protection design of nozzle of wind tunnel.

关 键 词：超声速风洞喷管 多流道冷却结构 气热耦合-结构热分析 多目标优化设计 响应面模型近似方法 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]