论文部分内容阅读
采用数值模拟的方法对液体火箭发动机燃烧室内湍流两相流动与燃烧过程进行了分析，同时研究了燃烧室内高频不稳定燃烧现象。气相控制方程用欧拉坐标系下的Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组描述，液相控制方程在Ｌａｇｒａｎｇｉａｎ坐标系下描述，湍流模型采用高雷诺数的ｋ－ε双方程模型，并采用高压蒸发燃烧模型。通过数值模拟分析了当燃烧室处于稳态燃烧时从喷注面到喉部之间两相混合物的变化规律；当发生高频不稳定燃烧时所研究的控制体内混合气体和喷雾的量发生振荡，并且具有相同的频率和半个周期的相位差。
The turbulent two-phase flow and combustion process in the liquid rocket engine combustion chamber were analyzed by numerical simulation. The phenomenon of high-frequency instability combustion in the combustion chamber was also studied. The gas-phase control equation is described by the Navier-Stokes equations in the Eulerian coordinate system. The liquid-phase governing equations are described in the Lagrangian coordinate system. The turbulence model uses a high Reynolds number k-ε two-equation model and a high pressure evaporative combustion model. Through the numerical simulation, the variation law of the two-phase mixture between the injection surface and the throat when the combustion chamber is in steady state combustion is analyzed. When the high frequency instability combustion occurs, the amount of the mixture and the amount of the spray in the control body oscillates , And have the same frequency and half-cycle phase difference.