Abstract: Three dimensional Navier Stokes equations and one step fast non reversible chemical reactions were employed to describe the flow and the combustion of the pre burner of an oxygen /kerosene liquid rocket engine The equations were solved using SIMPLE method in the co located grids, then the detail distribution of gas parameters was obtained The results show that the structure is suitable and the temperature distribution in the outlet section of the pre burner is uniform and the mass weighted average temperature in this section is closed to the practical mass weighted average temperature The results also show arrangement of injectors on head of pre burner and second liquid oxygen injecting holes, flow and combustion of injectors and entrance parameters of second liquid oxygen injecting holes exert a tremendous influence on well distribution of gas temperature and other parameters

Key words: Liquid propellant rocket engine;Precombustion chamber;Three dimensional flow;Turbulent combustion;Reacting flow;Numerical simulation

摘要： 用三维湍流N S方程和单步快速不可逆化学反应描述液氧 煤油液体火箭发动机预燃室内的三维湍流和燃烧过程。采用同位网格和SIMPLE算法求解控制方程 ,得到了喷注单元和预燃室内参数的详细分布。结果表明 ,预燃室结构设计合理 ,其出口处燃气浓度、温度分布均匀 ,质量加权平均温度与实际温度接近。同时表明 ,预燃室头部的喷注单元和液氧二次喷注孔的结构排列 ,喷注单元的流动和燃烧状况 ,液氧二次喷注孔的入口参数等 ,对预燃室出口燃气温度等参数分布的均匀性影响很大

关键词: 液体推进剂火箭发动机;预燃室;三维流;湍流燃烧;反应流;数值仿真