湍流两相燃烧不稳定性分析

TURBULENCE TWO PHASE COMBUSTION INSTABILITY ANALYSIS

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。

Turbulence two phase flow and combustion process in a liquid rocket engine combustor are analyzed with numerical method, and combustion instability is also studied. The gas controlling equations are described under the Euler coordinate.The liquid phase controlling equations are described under the Lagrangian coordinate.The changing pattern of the two phase mixed gas and spray from the chamber head to throat is observed: when high frequency combustion instability occurs, the quantities of mixed gas and spray in the controlling volume will vibrate having the same frequency but half cycle difference.