补燃循环火箭发动机气液同轴式喷嘴声学特性研究  

Investigation on Acoustic Characteristics of Gas-Liquid Coaxial Injector of Staged Combustion Rocket Engine

作　　者：李龙飞[1] 陈建华[1] 周立新[1] 孙宏明[1] 

机构地区：[1]陕西动力机械设计研究所,陕西西安710100

出　　处：《火箭推进》2004年第6期5-10,共6页Journal of Rocket Propulsion

摘　　要：基于经典声学和振动理论,运用流体动力学基本方程描述燃气通道内气体的波动现象,建立了双组元同轴直流离心式气液喷嘴声学特性分析的物理、数学模型,采用四端网络方法进行了计算。对单喷嘴声学模拟试验结果进行了分析。结果表明,所建声学特性分析模型用于分析喷嘴波动过程是可行的;合适的通道长度和节流嘴直径对液氧／煤油补燃循环发动机高频燃烧不稳定性有明显的阻尼作用。Based on the fundamental acoustic and vibration theories,a physical and mathematical model of the acoustic characteristics for a bipropellant gas-liquid coaxial swirl injector was developed.The general form fluid dynamic governing equations were adopted to deal with acoustic wave in the model.The four-poles net method was used to solve the equations.The experimental results of a single injector have been analyzed and discussed.The results showed that the appropriate channel length and the diameter of the entrance throttle of the injector would evidently restrain the high-frequency combustion instability of LOX/RP-1 propellant rocket Engine.

关 键 词：液体火箭发动机 气液喷嘴 高频燃烧不稳定性 声学特性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] V432