LRE模型燃烧室燃烧过程数值模拟

NUMERICAL SIMULATION OF COMBUSTION PROCESS IN LRE TEST COMBUSTION CHAMBER

建立了任意斜交曲线坐标系下液体火箭发动机（ＬＲＥ）内部工作过程的气液两相湍流化学反应流模型。应用该模型对气氢液氧模型燃烧室内部燃烧过程进行了数值模拟，得到了全流场的速度分布图形、燃气组分等值线、流场等温线、流场等压线、流场等马赫数线、壁面温度与径向平均温度曲线和燃烧效率曲线。计算结果表明：用数值模拟方法分析ＬＲＥ内部工作过程是可行的。

Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.By means of this model,numerical simulation of the combustion flow process in LO x/GH 2 test rocket engine has been accomplished.From the simulation,velocity patterns,contour maps of gas species concentration,temperature,pressure,Mach number,combustion efficiency,and plots of wall temperature and average radiateion temperature,and plot of spray vaporization are obtained.