Visualization Test Study on Two-Phase Flow Behaviors Inside Cryogenic Tank Under High Heat Flux

QU Miao; WANG Lei; SUN Peijie; YAN Li; WANG Qixiao; LI Yanzhong

doi:10.7652/xjtuxb202309007

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Visualization Test Study on Two-Phase Flow Behaviors Inside Cryogenic Tank Under High Heat Flux

更新时间：2025-07-09

- Visualization Test Study on Two-Phase Flow Behaviors Inside Cryogenic Tank Under High Heat Flux
- Vol. 57, Issue 9, Pages: 62-70(2023)
- 作者机构：
  
  1. 西安交通大学制冷与低温工程系,西安,710049
  2. 上海宇航系统工程研究所,上海,201109
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202309007
  CLC： V511+.6
- Online First：10 September 2023，
  
  Published：2023
- 稿件说明：
移动端阅览
QU Miao, WANG Lei, SUN Peijie, et al. Visualization Test Study on Two-Phase Flow Behaviors Inside Cryogenic Tank Under High Heat Flux[J]. 2023, 57(9): 62-70.
DOI：

QU Miao, WANG Lei, SUN Peijie, et al. Visualization Test Study on Two-Phase Flow Behaviors Inside Cryogenic Tank Under High Heat Flux[J]. 2023, 57(9): 62-70. DOI： 10.7652/xjtuxb202309007.

摘要

为研究大热流下低温推进剂贮箱箱内流体温度分层与沸腾气泡特征

以液氮为试验流体

搭建了低温贮箱变热流可视化相态观测平台

通过改变吹风温度与吹风速度

实现了1～16 kW·m

-2

热流边界调节

与火箭升空过程中承受气动热流冲击基本一致。试验结果表明:低温贮箱壁面受大热流作用

并不一定产生沸腾气泡; 当壁面热流密度小于2 kW·m

-2

直至液体主体过冷度降至1 K时

近壁区才有气泡产生; 壁面热流密度达到16 kW·m

-2

以上后

即使液体主体区过冷度超过10 K

近壁区也可能产生沸腾气泡; 当液体主体存在较大过冷度时

火箭升空过程的气动加热仅会造成近壁区出现气泡; 在对低温贮箱增压时

提高增压气体注入速率

加快增压进程有利于延缓近壁区液体温升与沸腾发生。此外

建立了一种预测沸腾气泡发生边界的经验模型

可对裸壁贮箱在大热流下是否发生推进剂沸腾提供初步预测

从而为火箭贮箱绝热方案设计提供支撑。

Abstract

In order to investigate the thermal stratification and boiling bubble features in the cryogenic propellant tank under great heat flux conditions

a visual platform was built

using liquid nitrogen as the test fluid. By adjusting the blowing temperature and speed

a heat flux boundary range of 1—16 kW·m

-2

was achieved

which was basically consistent with the aerodynamic heat flow impact during rocket launching. The results show that a high heat flux at the tank wall surface does not necessarily bring about boiling bubbles; when the heat flux density is less than 2

kW·m

-2

bubbles are generated in the near-wall region until the subcooling degree of the bulk liquid decreases to 1 K; comparatively

when the heat flux density exceeds 16 kW·m

-2

a high subcooling degree of 10 K of the bulk liquid could yield boiling bubbles. When there is a large degree of subcooling in the bulk liquid

the aerodynamic heating during rocket launch only causes bubbles in the near-wall region. Increasing the pressurized gas injection rate during the pressurization period of the cryogenic tank could postpone the liquid temperature rise as well as boiling occurrence in the near-wall region. In addition

an empirical model was established to describe the boundary of boiling bubbles

which can offer preliminary predictions on whether propellant boiling occurs in bare-wall storage tanks under high heat flux

thus providing support for the design of the insulation scheme for the rocket tank.

关键词

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references

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