高速二维喷管主动冷却数值模拟

徐大川; 顾蕴松; 陈景祥

doi:10.7638/kqdlxxb-2024.0196

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高速二维喷管主动冷却数值模拟

研究论文 | 更新时间：2026-05-28

- 高速二维喷管主动冷却数值模拟
- Numerical simulations of active cooling for a two-dimensional high-speed nozzle
- 空气动力学学报 2025年43卷第6期页码：28-34
- 作者机构：
  
  1. 南京航空航天大学航空学院,南京,210016
  2. 中国空气动力研究与发展中心设备设计与测试技术研究所,绵阳,621000
- 作者简介：
  
  徐大川（1985—），男，安徽界首人，博士研究生，研究方向：空气动力学. E-mail：xudachuan@nuaa.edu.cn
  陈景祥*，副研究员，研究方向：强化传热传质. E-mail：jingxiangchen@zju.edu.cn
- 基金信息：
  
  国家自然科学基金（52106215）
- DOI：10.7638/kqdlxxb-2024.0196
  中图分类号： TK121
- 纸质出版：2025
- 稿件说明：
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徐大川, 顾蕴松, 陈景祥. 高速二维喷管主动冷却数值模拟[J]. 空气动力学学报, 2025, 43(6): 28−34.

XU Dachuan, GU Yunsong, CHEN Jingxiang. Numerical simulations of active cooling for a two-dimensional high-speed nozzle[J]. 2025, 43(6): 28-34.
徐大川, 顾蕴松, 陈景祥. 高速二维喷管主动冷却数值模拟[J]. 空气动力学学报, 2025, 43(6): 28−34. DOI： 10.7638/kqdlxxb-2024.0196

XU Dachuan, GU Yunsong, CHEN Jingxiang. Numerical simulations of active cooling for a two-dimensional high-speed nozzle[J]. 2025, 43(6): 28-34. DOI： 10.7638/kqdlxxb-2024.0196.

摘要

针对地面试验设备中高速、高总温二维喷管的热防护需求，为降低喷管壁面温度，开展了喷管模型在不同工况下的主动冷却数值模拟研究。通过在壁板设计与气流方向垂直的矩形冷却通道，研究不同冷却工况对壁面温度分布、壁面热流密度分布以及出口马赫数分布的影响。结果表明：采用局部冷却模式时，相比绝热工况，喉部最高温度由469.1 K下降至372.5 K，显著降低了喷管喉部区域内壁面温度，提高了壁面温度场均匀性；采用全局冷却模式时，虽然可以提高壁面温度分布的均匀性，减小壁板内的热应力，但会影响出口下游温度和速度边界层厚度，导致核心流区域马赫数均匀性降低从而恶化流场品质。本研究可为高温长时间运行的高马赫数喷管热防护优化提供一定的设计参考。

Abstract

To meet the thermal protection requirements of high-speed and high-temperature two-dimensional nozzles in ground test facilities

a numerical study was conducted to evaluate the active cooling performance under different operating conditions. Rectangular cooling channels

perpendicular to the airflow direction

were designed within the wall panels to investigate the effects of different cooling configurations on wall temperature distribution

wall heat flux distribution

and exit Mach number distribution. The results indicated that localized cooling significantly reduced the maximum throat temperature from 469.1 K under adiabatic conditions to 372.5 K

effectively decreasing the wall temperature in the throat region and improving temperature uniformity. While global cooling enhanced the uniformity of wall temperature distribution and reduced thermal stress within the wall panels

it adversely affected the downstream temperature and velocity boundary layer thickness

leading to a deterioration of Mach number uniformity in the core flow region and a degradation of flow field quality.

关键词

Keywords

references

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