结构对固体火箭发动机可视化喷管两相流动的影响

李想; 李军伟; 李强; 韦彭威; 陈晨; 付青山

doi:10.7527/S1000-6893.2025.32185

航空学报 >

2026 , Vol. 47 >Issue 3: 132185 - 132185

DOI: https://doi.org/10.7527/S1000-6893.2025.32185

流体力学与飞行力学

结构对固体火箭发动机可视化喷管两相流动的影响

李想 ,
李军伟 ,
李强 ,
韦彭威 ,
陈晨 ,
付青山

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^1.北京理工大学宇航学院，北京 100081
^2.北京理工大学重庆创新中心，重庆 401120
^3.西安航天动力技术研究所固体推进全国重点实验室，西安 710025
^4.西安近代化学研究所燃烧与爆炸技术重点实验室，西安 710065

．E-mail： david78lee@bit.edu.cn

收稿日期: 2025-04-30

修回日期: 2025-05-19

录用日期: 2025-07-21

网络出版日期: 2025-07-31

基金资助

省部级项目

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Influence of structure on two-phase flow in visual nozzle of solid rocket motor

Xiang LI ,
Junwei LI ,
Qiang LI ,
Pengwei WEI ,
Chen CHEN ,
Qingshan FU

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^1.School of Astronautics，Beijing Institute of Technology，Beijing 100081，China
^2.Beijing Institute of Technology Chongqing Innovation Center，Chongqing 401120，China
^3.National Key Laboratory of Solid Rocket Propulsion，The Institute of Xi’an Aerospace Solid Propulsion Technology，Xi’an 710025，China
^4.Science and Technology on Combustion and Explosion Laboratory，Xi’an Modern Chemistry Research Institute，Xi’an 710065，China

E-mail： david78lee@bit.edu.cn

Received date: 2025-04-30

Revised date: 2025-05-19

Accepted date: 2025-07-21

Online published: 2025-07-31

Supported by

Provincial or Ministerial Level Project

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摘要

为了了解固体火箭发动机喷管内两相流场的速度分布，设计了一种二维平面可视化喷管，建立了针对喷管流场的速度在线测试系统，采用含氧化铝颗粒的低燃温固体推进剂，进行发动机点火实验，通过粒子图像测速（PIV）技术，获得了喷管扩张段内部分区域的流场速度，并采用数值仿真方法，研究了可视化喷管侧面盖板的截断长度、喷管形状对两相流场的影响。研究结果表明：实验测得的喷管内流场最高轴向速度达到了1 850 m/s，流场内混合有碳烟团和氧化铝颗粒，随着碳烟团的浓度沿纵向加重，流场区域的图像灰度由明转暗；减小可视化喷管侧面盖板的截断长度，使截断初始位置远离喷管喉部，颗粒在扩张段的扩散角由24.3°减小至21.5°，颗粒轨迹更向直边壁面集中；形状会对颗粒在拉瓦尔喷管中的流动造成影响，在半边方形喷管的收敛段及喉部位置处，受直边壁面的约束，颗粒会与壁面发生反复碰撞，形成暂时“滞留”在喉部区域的现象，将喷管形状由半边方形改为全尺寸方形后，颗粒较燃气速度的最大滞后值减小了46.9%。

关键词： 固体火箭发动机; 拉瓦尔喷管; 气-固两相流; PIV技术; 高速复杂流场

本文引用格式

李想 , 李军伟 , 李强 , 韦彭威 , 陈晨 , 付青山 . 结构对固体火箭发动机可视化喷管两相流动的影响[J]. 航空学报, 2026 , 47(3) : 132185 -132185 . DOI: 10.7527/S1000-6893.2025.32185

Abstract

To investigate the velocity distribution in the two-phase flow field of the solid rocket motor nozzle， a two-dimensional planar visual nozzle was designed， and an online system for measuring velocity of the nozzle flow field was established. The hot-firing test was carried out using a low combustion temperature solid propellant containing alumina particles. The flow field velocity in the expansion section inside the nozzle was obtained by the Particle-Image Velocimetry （PIV）. The influence of the truncated length of the side cover and shape of the visual nozzle on the two-phase flow field is studied by numerical simulation method. The research results show that the experimentally measured maximum axial velocity within the nozzle reached 1 850 m/s. The internal flow field contained a mixture of soot agglomerates and aluminum oxide particles， and as the soot concentration increased in the streamwise direction， the image grayscale intensity of the flow field gradually decreased from bright to dark. The numerical results indicate that reducing the truncated length of the side cover plate of the visual nozzle， thereby shifting the truncated position farther away from the nozzle throat， decreases the diffusion angle of particles from 24.3° to 21.5°， leading to a stronger concentration of particle trajectories toward the straight-line wall. The nozzle geometry was found to exert a pronounced influence on particle transport within the Laval nozzle. In the converging section and near the throat of the half-square nozzle， particles experienced repeated collisions with the straight wall due to geometric confinement， leading to a temporary residence or “particle trapping” phenomenon in the throat region. When the nozzle configuration was modified from a half-square to a full-square geometry， the maximum velocity lag of the particles relative to the gas was decreased by 46.9%.

Key words： solid rocket motor; Laval nozzle; gas-solid two-phase flow; PIV technology; high-speed complex flow field

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