小推力发动机膜冷却工程算法研究

为满足工程上对推力室内部传热流动分析的要求,应用分层流动理论,结合半经验传热和化学反应平衡模型,建立了分析小型液体火箭发动机推力室膜冷却的传热模型。以气氧/煤油发动机为例,初步实现了对定常情况下膜冷却过程的模拟。计算表明,冷却剂的质量分数,燃气的流动状态,喷注器尺寸等因素对冷却效果和发动机总体性能有重要影响。研究结果可为新一代小型液体火箭发动机的研制提供参考。

Engineering calculating method for film cooling in small thrust rocket engine

To meet the requirement of internal heat transfer analysis in chamber,based on stratified layers theory and in combination with semi-empirical heat transfer model and chemical equilibrium model , a heat transfer model was established to analyze the film cooling performance of the thruster. Process of the film cooling in a GOX/kerosene rocket engine at the instance of fixed constants was simulated. The computation of characteristics of heat transfer near inner wall has been realized. The influences of certain factors such as mass fraction, gas flow status on the efficiency of film cooling and the integral performance of the rocket engine were analyzed. The result may provide reference for the development of new generation of small liquid rocket engines.