Combustion process inside kerosene-GOx rocket combustor with kerosene film cooling is studied, and a modeling approach is proposed. The paper suggests to use the Lagrangian particle tracking technique to model fuel film behavior while the continuous fluid is simulated via the Navier-Stokes system of Favre-averaged equations. The approach is validated over the 12 experimental regimes by the criterions of characteristic velocity and pressure. The numerical study of film mass flow using the applied methodology shows significant influence on the adiabatic wall temperatures and relatively low impact on the pressure. In general, due to the application of the Lagrangian tracking and mostly simple models for main physical phenomena, the calculation of operational processes becomes fast and robust yet precise enough for engineering studies, which is helpful for parameterized routine calculations during the design process.

研究了煤油-GOx火箭燃烧器内部燃烧过程及煤油膜冷却过程，提出了一种建模方法。该论文建议使用拉格朗日粒子跟踪技术对燃料膜行为进行建模，而通过Favre平均方程式的Navier-Stokes系统模拟连续流体。通过特征速度和压力准则在12种实验方案中验证了该方法。使用所应用的方法对薄膜质量流进行的数值研究表明，对绝热壁温的影响很大，而对压力的影响则相对较小。总的来说，由于采用了拉格朗日跟踪技术，并且主要针对主要的物理现象建立了简单的模型，因此操作过程的计算变得快速，稳健，但对于工程研究而言足够精确，