摘要
通过一个简化的物理模型，运用计算流体动力学分析方法，研究了液体火箭发动机的不稳定燃烧现象，验证了该模型及分析方法的简捷和有效性。描述发动机燃烧室内气相流动过程的控制方程是非稳态准一维欧拉方程组，液相则用拉格朗日方法描述，方程组中的源项反映了气液两相耦合及液雾蒸发燃烧的影响。针对不稳定燃烧的机理，考察了压力脉动随着时间的推进对声学扰动的敏感性。计算格式采用两步积分的预测校正法进行选代求解。
A simplified physical model to study combustion instability of liquid rocket engines with CFD method is established in this paper. It is shown in the study that the model and the study method are both simple and efficient. In this study the gas flow in combustion chamber is described by unsteady quasi-one-dimensional Euler equations and Lagrangian method is used in liquid phase. The coupling of gas and liquid phases and the effects of vaprization /combustion of liquid spray are implicated in source terms of the equations. The influence of acoustical interaction on pressure fluctuation along with time is also investigated. The calculation is conducted with a two-step-integral predicted-correction method.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第2期11-16,共6页
Journal of Propulsion Technology
关键词
液体推进剂
火箭发动机
燃烧稳定性
流体动力学
Liquid propellant rocket engine, Combustion stability, Computational fluid dynamics, Numerical analysis
