燃气喷射推力矢量喷管气固两相流数值模拟

刘辉; 邢玉明

燃气喷射推力矢量喷管气固两相流数值模拟

刘辉,
邢玉明

北京航空航天大学航空科学与工程学院,北京 100191

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出版历程
- 刊出日期: 2013-01-28

Numerical simulation of gas-particle flow in hot gas injection thrust vector nozzle

School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 利用Euler-Lagrangian方法模拟了固体火箭发动机燃气喷射推力矢量喷管气固两相内流场,研究了固体颗粒对喷管推力矢量性能的影响.气相采用Roe格式和MUSCL (monotone upstream-centred schemes for conservation laws)插值进行空间2阶迎风离散,时间推进采用隐式时间格式;固体颗粒相采用随机轨道模型计算颗粒轨迹,并与气相进行双向耦合.结果表明:固体颗粒的存在使弓形激波强度增强,但降低了推力矢量角和推力系数;颗粒质量分数相同时,粒径越大,推力矢量角和推力系数越大;颗粒直径相同时,颗粒质量分数越大,推力矢量角和推力系数越小.
- 固体火箭发动机 /
- 推力矢量喷管 /
- 燃气喷射 /
- 气固两相 /
- 数值模拟
Abstract: The gas-particle inner flowfield of gas injection thrust vector nozzle in solid rocket engine was simulated using Euler-Lagrangian method,and the effect of solid particle on thrust vector performance was studied.The Roe scheme and monotone upstream-centred schemes for conservation laws(MUSCL)method were used for secondary-order accuracy spatial discretization for gas phase,and the implicit scheme was employed for time marching.The stochastic trajectory model and two-way coupled with gas phase were employed for particle phase.The results indicate that the strength of bow shock is increased due to solid particles,but the thrust vector angle and thrust coefficient are decreased;thrust vector angle and thrust coefficient increase with the particle diameter increasing under the same mass fraction of particle condition;thrust vector angle and thrust coefficient decrease with the mass fraction of particle increasing under the same particle diameter condition.
- solid rocket motor /
- thrust vector nozzle /
- hot gas injection /
- gas-particle two phase /
- numerical simulation

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参考文献(15)

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