喷水系统对W形地下空间热发射流场的影响

doi:10.12382/bgxb.2022.0014

摘要/Abstract

摘要：

采用喷水系统改善导弹地下空间热发射过程的流场,以达到削减压力脉冲峰值、缓解压强振荡和降低流场温度的目的,即减压、降温。结合三维黏性可压缩Navier-Stokes方程、Mixture多相流模型和相变模型,建立气-液两相流控制方程组,并用燃气射流缩比试验数据验证数学模型和数值方法的有效性,采用计算流体力学数值计算方法分析喷水系统对导弹地下空间发射过程流场环境的影响。研究结果表明:在W形地下空间底部建立喷水系统,可以很好地改善导弹地下热发射过程空间内流场环境特性;喷水系统对初始超压现象有很好地抑制效果,弹底压强振荡由8次减少到4次,压强没有产生剧烈振荡,在1atm上下缓慢变化,最大压强仅为1.20×10⁵Pa左右,大大削减了初始超压峰值,并降低了压强振荡的频率和幅值,实现了减压效果;通过液态水剧烈汽化、动量交换等过程,喷水系统强烈而有效地抑制了燃气反溅现象,燃气被约束在筒底位置,导弹底部的最高温度从3000K降低到了400K左右,实现了降温效果。

关键词: W形地下空间, 燃气射流, 喷水系统, 多相流, 汽化

Abstract:

The water spray system is used to improve the flow field in the thermal launch process of missiles in underground spaces, with the aim of reducing the peak value of pressure pulse, alleviating pressure oscillation, and reducing the temperature of flow field through “decompression and cooling”. In this study, a gas-liquid two-phase flow control equation is established by combining the three-dimensional viscous compressible Navier-Stokes equation, mixture multiphase flow model, and phase change model. The mathematical model and numerical method are validated using gas jet scaling test data. Computational fluid dynamics (CFD) numerical calculation method is used to analyze the influence of the water spray system on the flow field environment during the missile’s underground space launch process. The results show that the environmental characteristics of the flow field in the underground space during the thermal launch of the missile are effectively improved by establishing a water spray system at the bottom of the W-shaped underground space. The water spray system has a good suppression effect on the initial overpressure phenomenon. The bottom pressure oscillation is reduced from 8 times to 4 times. The pressure changes slowly up and down at 1 atm, with the maximum pressure only about 1.20×10⁵Pa. The initial overpressure peak is reduced, and the frequency and amplitude of the pressure oscillation are reduced, achieving the decompression effect. Through the process of violent vaporization of liquid water and momentum exchange, the phenomenon of gas backsplash is strongly and effectively suppressed by the water spray system. The gas is confined at the bottom of the cylinder, and the maximum temperature at the bottom of the missile is reduced from 3000K to about 400K, achieving the “cooling” effect.

Key words: W-shaped underground space, gas jets, water spray system, multiphase flow, evaporation

张曼曼, 姜毅, 史少岩, 邓月光. 喷水系统对W形地下空间热发射流场的影响[J]. 兵工学报, 2023, 44(4): 1158-1170.

ZHANG Manman, JIANG Yi, SHI Shaoyan, DENG Yueguang. Influence on Flow Field of Hot Launch in a W-Shaped Underground Space by Water Injection[J]. Acta Armamentarii, 2023, 44(4): 1158-1170.

图/表 24

图1 CFD控制方程求解流程图

Fig.1 Flowchart of the calculation process of CFD control equations

图2 W形地下发射筒几何模型

Fig.2 Geometric model of the W-shaped underground launcher

图3 发射筒喷水系统模型示意图

Fig.3 Model of water injection in the underground launcher

图4 发射筒剖面图边界条件示意图

Fig.4 Schematic diagram of boundary conditions of the launcher section

图5 发射筒网格模型

Fig.5 Meshing model of the launcher

图6 试验装置模型简图

Fig.6 Schematic of the experiment system

图7 底板温度测点示意图

Fig.7 Temperature measurement points of the bottom plate

图8 试验拍摄(左)与数值仿真(右)的波系结构对比

Fig.8 Comparison of wave structures acquired by test (left) and numerical simulation (right)

图9 试验测量值与仿真值对比

Fig.9 Comparison of the experimental measurement and numerical simulation values

表1 不同网格数量的基本参数

Table 1 Basic parameters of different grid numbers

参数	网格数量/万
参数	95	139	260	640
最小网格尺寸/mm	5.0	2.5	1.7	1.2
计算工时/h	60	96	144	240

图10 发射筒底部的压强变化

Fig.10 Pressure change at the bottom of the launcher

图11 导弹底部的温度变化

Fig.11 Pressure change at the bottom of the missile

图12 流场内的压强分布变化情况

Fig.12 Pressure distribution in the flow field

表2 监测点信息

Table 2 Monitoring point information

序号	监测点名称	坐标值/m	位置
1	missile-bottom	(0,0,0.12)	导弹底部的中心点
2	point-iop	(0,0,-0.16)	承重层与导流锥顶端连线的中点

表3 监测点missile-bottom前3个压力峰值的比较

Table 3 Comparison of the first three pressure peaks of the monitoring point missile-bottom

工况	压强峰序号	时间/ms	压强峰值/10⁵Pa
	1	0.240	2.695
无喷水	2	0.818	3.677
	3	1.488	2.358
	1	0.280	1.998
有喷水	2	0.830	2.390
	3	1.550	1.240

图13 监测点在初始、发展和稳定3阶段压强变化

Fig.13 Pressure change during initial,development and stable stage of monitoring points

图14 流场内的燃气分布变化

Fig.14 Gas distribution in the flow field

表4 增设的监测点信息

Table 4 Additional monitoring point information

监测点名称	角度/(°)	高度/m	位置
missile-90-1	90	0.3	导弹侧面的底部

图15 监测点的温度变化

Fig.15 Temperature change of the monitoring points

图16 流场内的温度分布变化(图中黑色的等值线为汽化速率0.01,单位为kg/(m3·s))

Fig.16 Temperature distribution in the flow field (The black contour refers to the vaporization reaction rate of 0.01kg/(m3·s))

表5 典型时刻液态水汽化反应速率及射流中间区域发生汽化速率的最高位置z值

Table 5 Liquid water vaporization reaction rate at typical moments and the highest position z value where the vaporization reaction rate occurs in the middle area of the jet

典型时刻/ms	液态水汽化速率/(kg·m^-3·s^-1)		最高位置 z值/mm
典型时刻/ms	最大值	最小值	最高位置 z值/mm
0.2	0.097×10^-8	-2.768×10^-8	81.6
0.8	0.358×10^-7	-2.302×10^-7	75.6
2.0	0.649×10^-7	-2.735×10^-7	63.6
5.3	1.883×10^-7	-5.200×10^-7	-8.8
19.0	1.758×10^-6	-3.006×10^-6	65.0
40.0	1.516×10^-7	-6.310×10^-7

图17 接触面上的温度云图

Fig.17 Temperature contours of the contact surface

图18 流场内汽化的水量比例变化

Fig.18 Proportional change of vaporized water in the flow field

图19 接触面的变化过程

Fig.19 Change process of the contact surface

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