火箭推进

为研究Al/AP粉末发动机燃料输送方式对粉末分散及混合效果的影响,利用气相控制方程、湍流模型、欧拉模型,对金属粉末发动机粉末燃料喷射掺混过程进行了详细的数值模拟。数值计算结果表明:固相体积分数和喷射入口有无锥体结构对流场参数具有较大影响。随着Al/AP粉末入口固相质量分数增加,粉末混合区域由燃烧室尾部向燃烧室头部移动。入口处安装锥体有利于粉末在燃烧室内分散,燃烧室头部颗粒相质量分数增加,轴线上平均固相质量分数降低,喷管前粉末局部积聚现象消失。

In order to study the effect of fuel delivery mode on the powder dispersion and mixing effect of Al/AP powder engine, the gas powder control equation, turbulence model and Euler model were used to carry out a detailed numerical simulation of the fuel injection blending process in the metal powder engine.The numerical results show that the solid phase volume fraction and the cone structure at the injection inlet have a great influence on the flow field parameters.With the inlet solid phase mass fraction of AI/AP powder improving, the mixing zone of powder moves from the end to the head of the combustor.The cone installation at the inlet facilitates the dispersion of the powder in the combustor.If the mass fraction of the particle phase at the head of the combustor increases and the average solid phase mass fraction on the axis decreases, the local accumulation of powder in front of the nozzle disappears.

引言
1 几何模型
2 基本假设
3 控制方程
4 边界条件与初始条件
5 计算结果及讨论
6 结论

图1 Al/AP粉末发动机计算模型<br/>Fig.1 Calculation model of Al/AP powder engine

图1 Al/AP粉末发动机计算模型
Fig.1 Calculation model of Al/AP powder engine

图2 粉末喷射过程<br/>Fig.2 Powder injection process

图2 粉末喷射过程
Fig.2 Powder injection process

$图3 不同时刻轴向Al/AP混合物质量分数<br/>Fig.3 Mass fraction of axial Al/AP mixture at different time$

图3 不同时刻轴向Al/AP混合物质量分数
Fig.3 Mass fraction of axial Al/AP mixture at different time

图4 不同入口固相体积分数时的粉末喷射过程<br/>Fig.4 Powder injection process with different α

图4 不同入口固相体积分数时的粉末喷射过程
Fig.4 Powder injection process with different α

$图5 t=1 s时不同入口固相体积分数时的轴线颗粒相质量分数<br/>Fig.5 Axial mass fraction of particle phase with different αwhen t=1 s$

图5 t=1 s时不同入口固相体积分数时的轴线颗粒相质量分数
Fig.5 Axial mass fraction of particle phase with different αwhen t=1 s

图6 混合区域随α的变化<br/>Fig.6 Change of mixing area with different α

图6 混合区域随α的变化
Fig.6 Change of mixing area with different α

图7 入口安装锥体后的粉末流化过程<br/>Fig.7 Powder fluidization process after installing the conical structure at the combustor inlet

图7 入口安装锥体后的粉末流化过程
Fig.7 Powder fluidization process after installing the conical structure at the combustor inlet

$图8 轴向Al/AP混合物质量分数<br/>Fig.8 Axial mass fraction of Al/AP mixture$

图8 轴向Al/AP混合物质量分数
Fig.8 Axial mass fraction of Al/AP mixture

[1] MEYER M L.Powdered aluminum and oxygen rocket propellants:sub-scale com-bustion experiments:NASA-TM-106439 [R].USA:NASA,1993.
[2] GOROSHIN S, HIGGINS A J, LEE J H.Powdered magnesium-carbon dioxide propulsion concepts for mars mission:AIAA 99-2408[R].USA:AIAA,1999.
[3] MILLER T F, HERR J D.Green rocket propulsion by reaction of Al and Mg powders and water:AIAA 2004-4037 [R].USA:AIAA, 2004.
[4] 申慧君, 夏智勋, 胡建新, 等.粉末燃料冲压发动机理论性能分析[J].推进技术, 2007, 28(2):181-185.
[5] 缪万波, 夏智勋, 郭健, 等.金属/水反应冲压发动机理论性能计算与分析[J].推进技术, 2005, 26(6):563-566.
[6] 朱卫兵, 张永飞, 陈宏, 等.双脉冲发动机内流场研究[J].弹箭与制导学报, 2012, 32(1):114-118.
[7] 孙娜, 娄永春, 孙长宏, 等.某双脉冲发动机燃烧室两相流场数值分析[J].固体火箭技术, 2012, 35(3):335-338.
[8] 杨晋朝, 夏智勋, 胡建新.粉末燃料冲压发动机内镁粉尘云层流燃烧模型[J].国防科技大学学报, 2013, 35(5):13-19.
[9] 孔龙飞, 夏智勋, 胡建新, 等.驻涡火焰稳定器式粉末燃料冲压发动机两相流数值模拟[J].固体火箭技术, 2013, 36(1):32-36.
[10] 李芳, 胡春波, 何国强.Mg粉/CO2粉末火箭发动机性能分析[J].固体火箭技术, 2010, 33(4):414-418.
[11] 李悦, 胡春波, 孙海俊, 等.粉末火箭发动机燃烧室燃烧流动特性研究[J].固体火箭技术, 2014, 37(6):792-796.
[12] 李芳, 胡春波, 何国强, 等.Mg粉/CO2点火燃烧性能实验研究[J].固体火箭技术, 2011, 34(2):193-196.
[13] 冷林涛, 翁春生, 白桥栋, 等.单组元粉末发动机内流场数值模拟研究[J].弹道学报, 2017, 29(2):58-64.
[14] 徐学文, 牟俊林, 任建存, 等.固体火箭发动机喷管瞬态流场特性分析[J].火箭推进, 2015, 41(5):49-53.

备注

引言

1 几何模型

2 基本假设

3 控制方程

4 边界条件与初始条件

5 计算结果及讨论

6 结论

期刊信息