Simulation study on the spray and mixing characteristics of a liquid-liquid throttleable pintle injector
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摘要:
针对应用日益广泛的变推力液体火箭发动机，建立了简化的液液型可调针栓单元平面推力室的仿真模型并开展了仿真计算。分析并阐明了液液型可调针栓喷雾的喷雾、流动及混合特性，得出了液膜角度与动量比对喷雾特性、流动特性和混合特性的影响。结果表明：在喷雾特性上，可调针栓存在一个特有的富氧低速流动区，其流体破碎效果受动量比影响；在流动特性上，可调针栓套筒下方有独特的回流区，其涡量强度随动量比增大而增强，而液膜角度变化影响不大，液膜角度和动量比的变化会影响撞击点附近的径向速度，进而改变不同区域的流量；从混合特性上看，环缝角度增加、理论煤油空间利用率下降，同时动量比从1.5增加到3.0，煤油利用率先上升后下降，最佳值出现在2.37左右。
Abstract:With the growing use of throttleable liquid rocket engines, a simplified physico-mathematical model for a plane thruster chamber’s unit, equipped with liquid-liquid throttleable pintle injectors, was formulated and numerically simulated. Spray, flow, and mixing characteristics of the injector spray were analyzed. The impact of film angle and momentum ratio on these characteristic was determined. Results revealed a distinct oxygen-rich low-velocity zone, with fluid crushing influenced by total momentum. Flow exhibited a unique recirculation zone beneath the injector sleeve, where vorticity was intensified with momentum ratio rise, unaffected by film angle. Variations in film angle and momentum ratio altered the radial velocity near the impact, affecting the flow rates regionally. Mixing efficiency declined with film angle increase, while kerosene space utilization initially rose then fell with momentum ratio from 1.5 to 3.0, peaking at about 2.37.
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图 8 不同网格分辨率条件下煤油和液氧的流量
Figure 8. Flow rate of kerosene and liquid oxygen at different grid resolutions
图 9 不同时间步长条件下煤油和液氧的流量
Figure 9. Flow rate of kerosene and liquid oxygen at different time steps
图 10 煤油、液氧体积分数为0.5的等值面图
Figure 10. Iso-surface diagrams of kerosene and liquid oxygen volume fraction of 0.5
图 12 煤油、液氧z方向切面体积分数云图
Figure 12. Contour of kerosene and liquid oxygen volume fraction on z-direction section
图 15 x方向流线及分区截面图
Figure 15. Streamline, partition, and section diagram in thex-direction
图 19 撞击点的中心面二维流线图
Figure 19. 2D streamline view of the center plane of the impact point
图 20 液氧相体积分数的局部流场流线图
Figure 20. Streamline diagram of the local flow field of the liquid oxygen phase volume fraction
图 21 喷雾半角的仿真值与公式预测值对比
Figure 21. Comparison of the spray half-angle between simulated value and predicted value of the formula
图 22 不同环缝角度的对称面的径向速度云图
Figure 22. Radial velocity contours of symmetry surfaces with different annular seam angles
图 23 不同γtm的对称面的径向速度云图
Figure 23. Radial velocity contours of symmetry surfaces for different γtm
图 24 不同环缝角度的涡量强度云图
Figure 24. Vorticity intensity contours at different annular seam angles
图 26 煤油液氧流量随环缝角度变化曲线图
Figure 26. Variation of kerosene and liquid oxygen flow rate with annular seam angle
图 27 理论煤油空间利用率η随环缝角度的变化曲线图
Figure 27. Theoretical kerosene space utilization η variation curve with annular seam angle
图 28 煤油液氧流量随动量比变化曲线图
Figure 28. Variation curves of kerosene and liquid oxygen flow rate with total momentum ratio
图 29 理论煤油空间利用率η随动量比变化曲线图
Figure 29. Theoretical kerosene space utilization rate η with momentum ratio
表 1 推力室与针栓设计参数
Table 1. Thrust chamber and pintle design parameters
参数 数值 煤油喷前压力pf/MPa 3.4 液氧喷前压力pO/MPa 3.6 单元液氧流量$\dot m_{\mathrm{O}} $/（g/s） 155 单元煤油流量$\dot m_{\mathrm{f}} $/（g/s） 53.9 
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表 2 针栓喷注单元的结构参数
Table 2. Pintle injection unit parameters
参数 数值 跳过距离Ls/mm 3.62 喷孔液膜距离Lt/mm 2.85 液膜厚度S/mm 0.48 孔高h/mm 3.00 孔宽w/mm 1.80 阻塞比γb 0.39 动量比γtm 2.37 环缝角度α/（°） 9.00
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表 3 计算域入口与出口的边界条件
Table 3. Computational domain boundary conditions
序号 边界名称 边界类型 流量/（g/s） 1 液氧入口 质量入口 155 2 煤油入口 质量入口 53.9 3 出口 压力出口
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表 4 物性参数表
Table 4. Physical characteristic parameter table
参数 航空煤油RP3 液氧 空气 参考温度T/K 298 100 298 密度ρ/（kg/m3） 764 1099 1.2 黏度μ/106 （Pa·s） 875.7 158 17.9
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表 5 水的物性参数表
Table 5. Physical characteristic parameter table of water
温度
T/K密度
ρ/（kg/m3）黏度
μ/（Pa·s））表面张力
σ/（N/m）300 1000 0.001 0.076
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表 6 设计参数列表
Table 6. Design parameter setting table
算例 孔高/mm 孔宽/mm γtm α/（°） 1 3.0 1.8 2.37 6 2 3.0 1.8 2.37 8 3 3.0 1.8 2.37 9 4 3.0 1.8 2.37 10 5 3.0 1.8 2.37 12.5 6 3.0 1.8 2.37 15 7 3.0 1.8 2.37 18 8 4.7 1.8 1.5 9 9 3.6 1.8 2 9 10 2.8 1.8 2.5 9 11 2.4 1.8 3 9
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