低温液氧射流冷凝振荡特性及流型转变阈值研究

祝乘风; 徐元元; 雷刚; 厉彦忠; 王磊

doi:10.12465/j.issn.0253-4339.2025.05.142

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低温液氧射流冷凝振荡特性及流型转变阈值研究

更新时间：2025-09-29

- 低温液氧射流冷凝振荡特性及流型转变阈值研究
- Research on the Oscillation Characteristic and Flow Pattern Transition Threshold of Cryogenic Liquid Oxygen Jet Condensation
- 制冷学报 2025年46卷第5期页码：142-156
- 作者机构：
  
  1.航天低温推进剂技术国家重点实验室　北京　100076
  2.西安交通大学能源与动力工程学院　西安　710049
- 作者简介：
  
  厉彦忠，男，教授，西安交通大学能源与动力工程学院，029-82668738，E-mail：yzli-epe@mail.xjtu.edu.cn。研究方向：航天低温推进剂技术，低温两相流动换热。
- 基金信息：
  
  航天低温推进剂技术国家重点实验室基金(SKLTSCP 202207)
- DOI：10.12465/j.issn.0253-4339.2025.05.142
  中图分类号： TB657;V511⁺.6;V475.1
- 收稿日期：2024-06-04，
  
  修回日期：2024-07-18，
  
  录用日期：2024-09-02，
  
  纸质出版日期：2025-10-16
- 稿件说明：
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祝乘风, 徐元元, 雷刚, 等. 低温液氧射流冷凝振荡特性及流型转变阈值研究[J]. 制冷学报, 2025,46(5):142-156.

Zhu Chengfeng, Xu Yuanyuan, Lei Gang, et al. Research on the Oscillation Characteristic and Flow Pattern Transition Threshold of Cryogenic Liquid Oxygen Jet Condensation[J]. Journal of refrigeration, 2025, 46(5): 142-156.
祝乘风, 徐元元, 雷刚, 等. 低温液氧射流冷凝振荡特性及流型转变阈值研究[J]. 制冷学报, 2025,46(5):142-156. DOI： 10.12465/j.issn.0253-4339.2025.05.142.

Zhu Chengfeng, Xu Yuanyuan, Lei Gang, et al. Research on the Oscillation Characteristic and Flow Pattern Transition Threshold of Cryogenic Liquid Oxygen Jet Condensation[J]. Journal of refrigeration, 2025, 46(5): 142-156. DOI： 10.12465/j.issn.0253-4339.2025.05.142.

摘要

低温液体燃料运载火箭在飞行过程中常常会遇到纵向不稳定振动，严重威胁火箭的正常运行。这种振动现象具有典型的低频特性，常发生于推进剂管路中低温液氧射流冷凝过程。为了从源头上解决火箭低频振动问题，需要研究射流冷凝振荡特性及冷凝流型转变特征。通过引入高度函数法改进冷凝传质模型，实现相界面曲率分布的动态捕捉，建立了冷凝脉动频率与气液相界面曲率之间的关系，成功获取了9.8~10.6 Hz的低频振荡特性。研究结果表明：推进剂管路内存在3种典型的射流冷凝振荡流型：稳定脉动、气羽振荡、间歇回流。其中，回流和振荡流型压力幅值最高可达130 kPa，而稳定脉动的压力幅值仅为1~3 kPa。通过量纲分析可知，当无量纲结构参数

=2.2时，射流冷凝流型转换阈值

=7.3。当

7.3时，则会出现间歇回流振荡流型，此无量纲判据可准确表征低温液氧射流冷凝流型分布，为低温液体燃料火箭的设计提供了理论基础和技术支撑。

Abstract

Cryogenic liquid fuel launch vehicles encounter longitudinal unstable vibrations during flight

which is a serious threat to the normal operation of rockets. Such vibrations exhibit typical low-frequency characteristics and often occur during the jet condensation of cryogenic liquid oxygen in propellant pipelines. To solve this problem at the source

the characteristics of the jet condensation oscillation and flow pattern

transition must be investigated. Based on the height function method

a modified mass transfer model was used to dynamically capture the interfacial curvature. The relationship between the condensation pulsation frequency and two-phase interfacial curvature was established

and the frequency of the pressure oscillation was found to be 9.8-10.6 Hz. The results indicated that three typical types of jet condensation oscillations exist: stable pulsation

gas plume oscillation

and suck-back flow. The pressure amplitude of the suck-back and oscillation flows was up to 130 kPa

whereas that of the stable pulsation was only 1-3 kPa. From the dimensional analysis

the transition threshold of the flow pattern was

=7.3 when dimensionless structure parameter

=2.2. When

7.3

a suck-back oscillating flow pattern appeared. The dimensionless criterion could precisely predict the condensation flow pattern. This provides a theoretical basis and technical support for the design of cryogenic liquid fuel rockets.

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