火箭上升段含多孔板液氧贮箱增压输运数值研究

doi:10.11949/0438-1157.20241359

摘要/Abstract

摘要：

为了研究火箭上升段含多孔板贮箱中低温推进剂的反馈增压过程，建立三维多相流多组分模型并使用NASA氦气增压液氢罐实验数据进行验证。对多孔隔板等比缩小计算多组流速下液氧的压降特性并进行拟合获得渗透率与压力跃变系数耦合到数值模型中。上升段过载变化过程中不同高度液体经过多孔板流阻不同造成界面弯曲。过载增大在扩散型入口下端形成高温射流导致界面处液相区分层厚度在过载指向侧更厚。上升过程中，72 s前界面处相变以蒸发为主，之后以冷凝为主。多孔板的存在阻碍贮箱内热自然对流使得最终相变量减少17.68%，同时使得出口平均压强增加3%左右。

关键词: 低温推进剂, 组分输运, 相变, 热力学, 计算流体力学, 多孔介质

Abstract:

In order to study the feedback pressurization process in the ascent period of the rocket and the influence of the porous plate, this paper has established the 3D multi-phase, multi-component model to simulate the pressurized discharge of helium in the liquid oxygen tank. The tank pressurized discharge tests, conducted as Lewis research center, are applied to validate the numerical model. The temperature and consumption of helium are compared with the experimental results of 12% error. This verification can demonstrate the accuracy of the model proposed. And then, the porous plate is isometrically reduced, and a simplified model is constructed to calculate the pressure drop of liquid oxygen with multiple flow rates. The effect of the porous plate on the flow is limited to a very small region near the plate. The large pressure drop exists and calculated by the porous jump model coupling with the proposed model. The permeability ε and pressure jump coefficient c₂ in the porous jump model are acquired by fitting. The different flow resistance of the cryogenic propellant at different heights through the porous plate during the variation of overload results in bending of the interface. The temperature in the liquid phase remains almost constant, and the temperature in the vapor phase increases with the axis height increases along the direction of overload. The increasing overload leads to the high temperature jetting at the lower of the diffusion inlet. Thus, the thicker thermal stratified layer forms on the overload-directed side. The pressure in the cryogenic tank can be divided into three regions, with the pressure in the ullage remaining constant and the pressure in the liquid region rising as approaching the outlet. And the porous plate produces a sudden increase in the pressure. The phase change at the interface is dominated by evaporation until 72 s and condensation thereafter. Meanwhile, the existence of porous plate prevents the natural convection in the tank which increases the temperature at the interface. The increase in temperature results in that the evaporation dominates the phase change in the cryogenic tank. Correspondingly, the mass of phase change and outlet pressure increase 17.68% and 3% compared with the pressurized discharge process without porous plate, respectively. The present study is significant for the understanding of the pressurized discharge in cryogenic propellant tank and could provide recommendations for the design and optimization of pressurization systems and structure of porous plate for cryogenic propellants.

Key words: cryogenic propellant, species transfer, phase change, thermodynamics, computational fluid dynamics(CFD), porous media

中图分类号:

TK 123

郭松源, 周晓庆, 缪五兵, 汪彬, 耑锐, 曹庆泰, 陈成成, 杨光, 吴静怡. 火箭上升段含多孔板液氧贮箱增压输运数值研究[J]. 化工学报, 2025, 76(S1): 62-74.

Songyuan GUO, Xiaoqing ZHOU, Wubing MIAO, Bin WANG, Rui ZHUAN, Qingtai CAO, Chengcheng CHEN, Guang YANG, Jingyi WU. Numerical study on characteristics of pressurized discharge in liquid oxygen tank equipped with porous plate in the ascent period of rocket[J]. CIESC Journal, 2025, 76(S1): 62-74.

图/表 20

图1 液氧贮箱结构

Fig.1 Schematic diagram of liquid oxygen tank

图2 上升段增压输运示意图

Fig.2 The pressurized discharge process in the ascent period of rocket

表1 组分输运模型经验参数取值［13］

Table 1 Value of constants in the species transport model［13］

经验参数	取值
A	1.06036
B	0.15610
C	0.19300
D	0.47635
E	1.03587
F	1.03587
G	1.76474
H	3.89411

表2 流体热物理性质

Table 2 Thermo-physical properties of fluid

参数	液氧	氧气	氦气
密度/(kg/m³)	Boussinesq假设	理想气体状态方程	理想气体状态方程
比定压热容/(J/(kg·K))	1695.5	969.26	5195
热导率/(W/(m·K))	0.153	$k O 2$ (T)	k_He(T)
黏性系数/(μPa·s)	2.032×10^-5	$μ O 2$ (T)	μ_He(T)
摩尔质量/(g/mol)	32	32	4

表2 流体热物理性质

Table 2 Thermo-physical properties of fluid

参数	液氧	氧气	氦气
密度/(kg/m³)	Boussinesq假设	理想气体状态方程	理想气体状态方程
比定压热容/(J/(kg·K))	1695.5	969.26	5195
热导率/(W/(m·K))	0.153	$k O 2$ (T)	k_He(T)
黏性系数/(μPa·s)	2.032×10^-5	$μ O 2$ (T)	μ_He(T)
摩尔质量/(g/mol)	32	32	4

表3 固体热物理性质

Table 3 Thermo-physical properties of fluid

参数	2219Al	泡沫层
密度/(kg/m³)	2800	40
比定压热容/(J/(kg·K))	830	1470
热导率/(W/(m·K))	159	0.03

图3 液氧贮箱模型及边界条件

Fig.3 Geometric structure and boundary conditions of liquid oxygen tank

表4 增压输运过程初始条件设置

Table 4 Initial conditions in pressurized discharge

参数	2219Al初始条件设置
压强/kPa	430
体积分数	$H > 1.97 m, α g = 1, α l = 0 (气相区域) H < 1.97 m, α g = 0, α l = 1 (液相区域)$
温度	$H > 1.97 m, T = 88.6 ~ 300 K (线性分布) H < 1.97 m, T = 88.6 K$
氧气质量分数	$H > 1.97 m, Y O 2 = 1$

表4 增压输运过程初始条件设置

Table 4 Initial conditions in pressurized discharge

参数	2219Al初始条件设置
压强/kPa	430
体积分数	$H > 1.97 m, α g = 1, α l = 0 (气相区域) H < 1.97 m, α g = 0, α l = 1 (液相区域)$
温度	$H > 1.97 m, T = 88.6 ~ 300 K (线性分布) H < 1.97 m, T = 88.6 K$
氧气质量分数	$H > 1.97 m, Y O 2 = 1$

图4 贮箱内外实验与仿真温度分布对比

Fig.4 The comparison of temperature distribution along the axis and the wall with simulation and experiment

图5 不同网格数氦气质量消耗

Fig.5 The comparison of helium consumption calculated by different grid numbers

图6 缩比孔板示意图与网格图

Fig.6 Schematic diagram and mesh of an isometrically reduced porous plate

图7 不同流速流经孔板压差与速度云图

Fig.7 The pressure difference and velocity distribution at different velocity magnitude through porous plate

图8 轴线上压强与轴向速度

Fig.8 The pressure and axis velocity at the symmetry axis

图9 上升段增压输运过程气液界面分布（左侧为三维图，右侧为ZY平面截面图）

Fig.9 The variation of interface at three dimensional (left) and ZY cross sections (right) in the ascent period of pressurized dischrage

图10 过载随时间变化

Fig.10 The variation of acceleration at the upper stage

图11 增压输运过程中温度沿轴线分布

Fig.11 Variations of the tank axis temperature during pressurized discharge

图12 增压输运过程中氦气浓度沿轴线分布

Fig.12 Variations of the tank axis mass fraction of helium during pressurized discharge

图13 增压输运过程中温度与氦气浓度分布

Fig.13 The temperature and mass fraction of helium distribution during pressurized discharge

图14 上升段增压输运过程压强沿轴线分布

Fig.14 Variation of the tank axis pressure during pressurized discharge in the ascent period of rocket

图15 多孔板前后压差随时间变化

Fig.15 The difference in pressure over time before and after porous plate

图16 上升段安装多孔板与未安装多孔板增压输运过程的对比

Fig.16 The comparison of pressurized discharge process with and without the porous plate in the ascent period of rocket

参考文献 30

1	林恩承, 王文, 匡以武, 等. 低温输运管道预冷过程的气液两相数值分析[J]. 化工学报, 2021, 72(S1): 153-160.
	Lin E C, Wang W, Kuang Y W, et al. Numerical analysis of cryogenic two-phase precooling flow in a mini pipe[J]. CIESC Journal, 2021, 72(S1): 153-160.
2	汪彬, 李江道, 黄永华, 等. 节流参数对液氮贮箱热力排气系统运行特性的影响[J]. 化工学报, 2019, 70(S2): 101-107.
	Wang B, Li J D, Huang Y H, et al. Effect of throttle parameters on operating performance of thermodynamic vent system in liquid nitrogen tank[J]. CIESC Journal, 2019, 70(S2): 101-107.
3	Wang L, Ye S X, Ma Y, et al. CFD investigation on helium pressurization behaviors in liquid hydrogen tank[J]. Int. J. Hydrogen Energ., 2017, 42(52): 30792-30803.
4	肖明堃, 杨光, 黄永华, 等. 浸没孔液氧气泡动力学数值研究[J]. 化工学报, 2023, 74(S1): 87-95.
	Xiao M K, Yang G, Huang Y H, et al. Numerical study on bubble dynamics of liquid oxygen at a submerged orifice[J]. CIESC Journal, 2023, 74(S1): 87-95.
5	Chintalapati S, Kirk D. Parametric study of a propellant tank slosh baffle[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Hartford, CT. Reston, Virigina: AIAA, 2008: AIAA2008-4750.
6	Ohashi A, Furuichi Y, Haba D, et al. Experimental and numerical investigation on pressure change in cryogenic sloshing with a ring baffle[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference. Atlanta, GA. Reston, Virginia: AIAA, 2017: AIAA2017-4760.
7	Stewart M. Pressurization of a flightweight, liquid hydrogen tank: evaporation & condensation at the liquid/vapor interface[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference. Atlanta, GA. Reston, Virginia: AIAA, 2017: AIAA2017-4916.
8	Sato Y, Imai R, Nakata D, et al. Study on propellant supply system for small-scale supersonic flight experiment vehicle (development of design technology for LOX supply system)[J]. Int. J. of Microgravity Sci. Appl., 2020, 37(1): 370104
9	Wang L, Yan T, Wang J J, et al. CFD investigation on thermodynamic characteristics in liquid hydrogen tank during successive varied-gravity conditions[J]. Cryogenics, 2019, 103: 102973.
10	Wang L, Li Y Z, Zhao Z X, et al. Transient thermal and pressurization performance of LO₂ tank during helium pressurization combined with outside aerodynamic heating[J]. Int. J. Heat Mass Tran., 2013, 62: 263-271.
11	Liu Z, Yin X, Liu Y L, et al. Investigation on thermal behavior during pressurization discharge of liquid oxygen under different acceleration levels[J]. Microgravity Sci. Tec., 2022, 34(3): 27.
12	Liu Z, Feng Y Y, Lei G, et al. Fluid thermal stratification in a non-isothermal liquid hydrogen tank under sloshing excitation[J]. Int. J. Hydrogen Energ., 2018, 43(50): 22622-22635.
13	Guo S Y, Xiao M K, Xie F, et al. Optimization of helium consumption for feedback pressurization in liquid oxygen tanks[J]. Int. J. Heat Mass Tran., 2024, 230: 125739.
14	Konopka M, Noeding P, Klatte J, et al. Analysis of LN₂ filling, draining, stratification and sloshing experiments[C]//46th AIAA Fluid Dynamics Conference. Washington, D.C. Reston, Virginia: AIAA, 2016: AIAA2016-4272.
15	Himeno T, Ohashi A, Anii K, et al. Investigation on phase change and pressure drop enhanced by violent sloshing of cryogenic fluid[C]//2018 Joint Propulsion Conference. Cincinnati, Ohio. Reston, Virginia: AIAA, 2018: AIAA2018-4755.
16	Sippel M, Stappert S, Callsen S, et al. A viable and sustainable European path into space-for cargo and astronauts[C]//72nd International Astronautical Congress. Dubai, United Arab Emirates: IAC, 2021: IAC21-D2.4.4.
17	Behruzi P, Klatte J, Fries N, et al. Cryogenic propellant management sounding rocket experiments on TEXUS 48[C]//49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. San Jose, CA. Reston, Virginia: AIAA, 2013: AIAA2013-3904.
18	Manning R E, Ballinger I, Bhatia M, et al. Design of the Europa clipper propellant management device[C]//AIAA Propulsion and Energy 2019 Forum. Indianapolis, IN. Reston, Virginia: AIAA, 2019: AIAA2019-3858.
19	Zuo Z Q, Jiang W B, Huang Y H. Effect of baffles on pressurization and thermal stratification in cryogenic tanks under micro-gravity[J]. Cryogenics, 2018, 96: 116-124.
20	Gaulke D, Dreyer M E. CFD simulation of capillary transport of liquid between parallel perforated plates using Flow3D[J]. Microgravity Sci. Tec., 2015, 27(4): 261-271.
21	Hartwig J, Esser N, Jain S, et al. CFD modeling of bidirectional PMDs inside cryogenic propellant tanks onboard parabolic flights[J]. J. Spacecraft Rockets, 2024, 61(1): 296-312.
22	Hartwig J W. Liquid Acquisition Devices for Advanced in-Space Cryogenic Propulsion Systems[M]. New York: Academic Press, 2016.
23	Li J C, Liang G Z, Zhu P P, et al. Numerical investigation of the operating process of the liquid hydrogen tank under gaseous hydrogen pressurization[J]. Aerosp Science And Technology, 2019, 93: 105327.
24	Taylor A H, Cerro J A, Jackson L R. Analytical study of reusable flight-weight cryogenic propellant tank design[J]. J. Spacecraft Rockets, 1986, 23(2): 149-157.
25	Brackbill J U, Kothe D B, Zemach C. A continuum method for modeling surface tension[J]. J. Comput. Phys., 1992, 100(2): 335-354.
26	Li J C, Liang G Z. Simulation of mass and heat transfer in liquid hydrogen tanks during pressurizing[J]. Chinese Journal of Aeronautics, 2019, 32(9): 2068-2084.
27	Liu Z, Li Y Z, Jin Y H. Pressurization performance and temperature stratification in cryogenic final stage propellant tank[J]. Appl. Therm Eng., 2016, 106: 211-220.
28	Roudebush W.H., An analysis of the problem of tank pressurization during outflow[R]. Cleveland: Lewis Research Center, 1965: 6-11.
29	Yoon S H, Park K J. Effect of baffles on sloshing mitigation in liquid storage tanks[C]//Advanced Science and Technology Letters. Science & Engineering Research Support soCiety, 2015: 1-5.
30	Tanner P, Gorman J, Sparrow E. Flow-pressure drop characteristics of perforated plates[J]. Int. J. Numer. Method H., 2019, 29(11): 4310-4333.

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