固体火箭发动机喷管气固两相流动的数值模拟
Numerical simulation of gas-particle flow in nozzle of solid rocket motor
查看参考文献16篇
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文摘
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对颗粒相采用颗粒轨道模型,气相求解可压缩N-S方程组,计算方法采用显式Runge-Kutta时间推进法与有总变差衰减(TVD)性质的高精度MUSCL-Roe格式;自主开发了曲线坐标系下二维轴对称可压缩N-S方程组的解算器Solve2D,研究了固体火箭发动机喷管中颗粒相对流场的影响以及不同尺寸颗粒运动规律.结果表明:颗粒相对流场的影响主要表现在喷管喉部以及扩张段,和单相流场相比,沿轴线马赫数减小,且颗粒尺寸越小减少得越多;沿轴线气相温度升高,且颗粒尺寸越小温度升高越多;颗粒尺寸越小,无粒子区越小;颗粒越大与收缩段壁面碰撞越剧烈,无粒子区越大. |
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其他语种文摘
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In order to study the influences of particles on gas flow in nozzle of solid rock-et motor and the rules of particles flowing at different sizes, an Eulerian-Lagrangian ap-proach was employed, Particle trajectory model was used for particle phase and compressible N-S equations were solved. MUSCL-Roe total variation diminishing (TVD) scheme with high order accuracy, and two-stage, time-stepping Runge-Kutta method with TVD character have been used to solve two-dimensional axis symmetric compressible N-S equations by a home codes "Solve2D". Simulation results indicate that the influence of particle primarily lies in throat and expansion segments of nozzle. Compared to pure gas flow, Mach numbers de-creased along centerline, and the reduction became larger with smaller size particle. The gas temperature increased in two-phase flow, and the enhancement became higher with smaller size particles. The region without particles was smaller with smaller size particles. Big size particles had serious collision with wall of convergent region, and the region without parti-cles was larger. |
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来源
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航空动力学报
,2009,24(4):931-937 【核心库】
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关键词
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火箭发动机
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喷管
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两相流
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数值模拟
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颗粒轨道模型
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地址
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1.
北京理工大学,宇航科学与技术学院, 北京, 100081
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中国科学院力学研究所, 北京, 100190
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1000-8055 |
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学科
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航空 |
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基金
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国家自然科学基金
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文献收藏号
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CSCD:3592956
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参考文献 共
16
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