高超声速喷管冷却的优化设计  

Optimal Design of Hypersonic Nozzle Cooling

作　　者：尹茜 孟凡民[1] 刘新朝 李强[1] Yin Qian;Meng Fanmin;Liu Xinchao;Li Qi(Aero Science Key Laboratory of High Reynolds Aerodynamic Force at High Speed,AViC Aerodynamics Research Institute,Shenyang110034,China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《气动研究与试验》2025年第1期67-73,共7页Aerodynamic Research & Experiment

摘　　要：高超声速风洞中为了避免气流液化,需要提高气流总温;然而,过高的温度会破坏喷管结构进而影响风洞的流场品质。因此,在设计风洞时需要对喷管结构进行热防护分析。本文提出了一种喷管冷却结构,喷管分为4段,每段沿周向划分18条冷却水道。利用流固热耦合计算方法研究壁面材料、壁面厚度、冷却水量、水道布置等因素对喷管传热的影响。计算结果表明,当冷却水总流量从12kg/s增加到25kg/s时,喷管平均冷却效率提高了2.6%,压损增大了2.4×10~4Pa;冷却水道数量由18变成36时,喷管内壁面平均温度降低了17K;肋板宽度从2mm增加到10mm时,喷管内壁面平均温度降低了170K。根据研究结果提出喷管冷却结构的优化设计方法,为高超声速风洞中喷管热防护提供一定的参考。In high hypersonic wind tunnels,in order to avoid the liquidation of the gas flow,the total temperature of the gas flow needs to be increased;however,excessively high temperatures can destroy the nozzle structure and affect the quality of the wind tunnel flow field.Therefore,it is necessary to conduct thermal protection analysis on the nozzle structure when designing the wind tunnel.This paper proposes a nozzle cooling structure that is divided into four sections,with 18 cooling water channels per section along the circumferential direction.The influence of wall material,wall thickness,cooling water flow rate,water channel arrangement,etc.on the heat transfer of the nozzle is studied using a fluid-structure-thermal coupling calculation method.The calculation results show that when the total flow rate of cooling water increases from 12kg/s to 25kg/s,the nozzle cooling efficiency increases by 2.6%,while the pressure loss also increases by 2.4x10*Pa;when the number of cooling water channels increases from 18 to 36,the maximum temperature on the inner wall of the nozzle decreases by 17K;when the width of the rib is increased from 2mm to 10mm,the temperature on the inner wall of the nozzle decreases by 170k.Based on the research results,a method for optimizing the nozzle cooling structure is proposed,providing a certain reference for the thermal protection of the nozzle in high hypersonic wind tunnels.

关 键 词：喷管冷却 高超声速 流固热耦合 优化设计 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]