液体火箭发动机燃烧不稳定性分析模型  

AN ANALYSIS MODEL ON COMBUSTION INSTABILITY IN LIQUID ROCKET ENGINES

作　　者：赵文涛[1] 周进[1] 王振国[1] 庄逢辰[1] 

机构地区：[1]国防科技大学航天技术系

出　　处：《推进技术》1995年第2期11-16,共6页Journal of Propulsion Technology

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.

关 键 词：液体推进剂 火箭发动机 燃烧稳定性 流体动力学 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]