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深度过冷循环低温推进剂贮箱温场特性分析

张亮 汪彬 李杨 李超 沙赵明 罗云 王文

张亮, 汪彬, 李杨, 等. 深度过冷循环低温推进剂贮箱温场特性分析[J]. 航空动力学报, 2024, 39(8):20220588 doi: 10.13224/j.cnki.jasp.20220588
引用本文: 张亮, 汪彬, 李杨, 等. 深度过冷循环低温推进剂贮箱温场特性分析[J]. 航空动力学报, 2024, 39(8):20220588 doi: 10.13224/j.cnki.jasp.20220588
ZHANG Liang, WANG Bin, LI Yang, et al. Temperature field analysis of cryogenic propellant tanks with deep subcooling cycle[J]. Journal of Aerospace Power, 2024, 39(8):20220588 doi: 10.13224/j.cnki.jasp.20220588
Citation: ZHANG Liang, WANG Bin, LI Yang, et al. Temperature field analysis of cryogenic propellant tanks with deep subcooling cycle[J]. Journal of Aerospace Power, 2024, 39(8):20220588 doi: 10.13224/j.cnki.jasp.20220588

深度过冷循环低温推进剂贮箱温场特性分析

doi: 10.13224/j.cnki.jasp.20220588
详细信息
    作者简介:

    张亮(1977-),男,研究员,博士,主要从事运载火箭及飞行器总体设计研究。E-mail:13816349731@139.com

  • 中图分类号: V511.6

Temperature field analysis of cryogenic propellant tanks with deep subcooling cycle

  • 摘要:

    以某型号火箭液氧贮箱为例,对液氧在深度过冷循环过程中贮箱的降温特性进行仿真计算。以液氮为模拟工质,搭建低温推进剂过冷循环原理性缩比试验系统,通过实验数据验证数值模型的准确性。仿真分析了过冷循环流量及回流形式对贮箱降温速率及热分层特性的影响。研究表明:由于一级液氧贮箱筒段较长,贮箱内流体混合更加充分,液体温度均匀性良好;对于二级贮箱,由于其轴向长度较短,从输送管回流的部分深度过冷液氧直接通过贮箱上部抽液口被吸出,发生循环短路,导致贮箱温度始终无法降至70 K,贮箱内温度分层明显,温度均匀性较差,在对贮箱结构进行优化后,贮箱降温速率和温度均匀性提升明显。

     

  • 图 1  液氧贮箱外部循环过冷原理图

    Figure 1.  Schematic diagram of external loop sub-cooling of liquid oxygen tank

    图 2  一级、二级液氧贮箱物理模型(单位:mm)

    Figure 2.  Physical model of primary/secondary liquid oxygen tank (unit:mm)

    图 3  过冷加注原理性试验系统实物图

    Figure 3.  Picture of subcooled loading experimental system

    图 4  贮箱温度变化与网格数量的关系

    Figure 4.  Relationship between temperature variation and mesh number

    图 5  仿真结果与实验数据对比

    Figure 5.  Comparison of simulation results and experimental data

    图 6  一级液氧贮箱过冷循环温度变化情况

    Figure 6.  Temperature variation of subcooled cycle of primary liquid oxygen tank

    图 7  一级液氧贮箱过冷循环内部温度分布

    Figure 7.  Temperature distribution of subcooled cycle of primary liquid oxygen tank

    图 8  二级液氧贮箱过冷循环温度变化情况

    Figure 8.  Temperature variation of subcooled cycle of secondary liquid oxygen tank

    图 9  二级液氧贮箱过冷循环内部速度分布

    Figure 9.  Velocity distribution of subcooled cycle of secondary liquid oxygen tank

    图 10  不同回流形式时过冷循环贮箱温度变化

    Figure 10.  Comparison of temperature variation with different return form of subcooled cycle tank

    图 11  布置挡板时液氧贮箱内部温度分布

    Figure 11.  Temperature distribution of liquid oxygen tank with top baffled

    图 12  布置挡板时液氧贮箱内部速度分布

    Figure 12.  Velocity distribution of liquid oxygen tank with top baffled

    图 13  挡板不同位置时过冷循环贮箱温度变化

    Figure 13.  Comparison of temperature variation with different baffle position of subcooled cycle tank

    表  1  液氧贮箱过冷循环阶段边界条件

    Table  1.   Boundary conditions of external loop sub-cooling of liquid oxygen tank

    状态 一级液氧
    贮箱
    二级液氧
    贮箱
    加注容积/L 121000 20000
    箱底至发动机输送管高/m 13 3
    输送管/mm 320 120
    绝热层或箱壁外表面辐射率ε 0.8 0.8
    绝热结构厚度/mm 20 20
    绝热层外表面对太阳的热辐射吸收率αs 0.3 0.3
    绝热层表观导热系数/(W/(m·K)) 0.023 0.023
    箱壁导热系数/(W/(m·K)) 170 170
    环境温度/K 298 298
    下载: 导出CSV

    表  2  测量系统中传感器的精度

    Table  2.   Uncertainties in efficient cryogenic fluid storage test platform

    测量仪表 量程 精度
    PT100铂电阻 77~300 K ±0.1 K
    压力传感器 0~0.8 MPa 0.25% FS
    差压液位计 0~2 000 mm H2O ±0.075%
    下载: 导出CSV
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  • 收稿日期:  2022-08-14
  • 网络出版日期:  2023-11-27

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