对液氧 煤油液体火箭发动机的预燃室进行三维湍流流动与燃烧过程的数值模拟。流动采用圆柱坐标系中的三维N S方程组 ,并用k ε双方程湍流模型闭合 ,用同位网格和SIMPLE算法求解 ,源项进行线性化处理以便于收敛 ;离散后的方程采用SIP法求解 ;燃烧采用单步快速不可逆化学反应 ;喷注单元和预燃室头部的喷雾可以考虑液滴颗粒轨道模型 (PSIC)。针对液氧 煤油液体火箭发动机的预燃室建立了耦合计算软件 ,通过考核算例获得燃气流场、组分浓度场和温度场的合理分布 The numerical simulation of the three-dimensional turbulent flow and combustion process in the liquid-oxygen kerosene liquid rocket engine pre-combustion chamber was carried out. The three-dimensional Navier-Stokes equations in a cylinder coordinate system are used for the flow and are closed by the k ε two-equation turbulence model. The collocated grid and the SIMPLE algorithm are used to solve the problem. The source term is linearized for convergence. The discrete equation is solved by the SIP method. A single-step, irreversible chemical reaction is used; droplet particle orbit model (PSIC) can be considered for the spraying of the injection unit and pre-combustion chamber head. Aiming at the precombustion chamber of liquid oxygen kerosene liquid rocket engine, a coupling calculation software was established, and the reasonable distribution of gas flow field, component concentration field and temperature field