液氢/液氧火箭发动机喷雾燃烧过程三维数值模拟  

THREE DIMENSIONAL NUMERICAL SIMULATION ON SPRAY COMBUSTION IN A LOX HYDROGEN ENGINE

作　　者：刘卫东[1] 王振国[1] 周进[1] 

机构地区：[1]国防科技大学航天技术系

出　　处：《推进技术》1999年第1期19-23,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金

摘　　要：用三维湍流Ｎ－Ｓ方程及拟流体模型描述液体火箭发动机内部喷雾两相燃烧流动过程，两相之间的质量交换采用蒸发模型计算，气相化学反应速率采用Ａｒｒｈｅｎｉｕｓ公式计算。采用ＳＩＭＰＬＥＲ与ＩＰＳＡ算法求解两相控制方程并对氢氧发动机燃烧流动过程进行了三维数值分析，得到了发动机推力室内燃气参数的详细分布情况。结果表明对氢氧发动机而言，蒸发过程非常快，推进剂混合过程是燃烧过程的决定因素。Three dimensional Navier Stokes equations and two phase fluid model which considered the liquid propellant spray as continuous phase were employed to describe the gas/liquid turbulent flow in the thrust chamber of liquid rocket engine.The mass transfer between the two phases was calculated by the droplet evaporation model and the chemical reaction rate was given by the Arrhenius model.The equations were solved using SIMPLER and IPSA algorithm with the detail distribution of gas parameters obtained.The results show that the oxygen evaporates very fast and the decisive factor of the combustion rate is the mixing process of the propellants.

关 键 词：氢氧发动机 两相燃烧 数值仿真 喷雾燃烧 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]