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基于离散颗粒模型,采用单元内颗粒源法对某氢氧火箭发动机湍流两相燃烧流场进行了三雏全尺寸数值仿真。液氧雾化液滴采用Rosin-Rammler分布模型,其质量平均直径采用同轴直流喷嘴雾化模型计算;考虑液氧高压蒸发过程;燃烧速率采用湍流脉动机制和Arrhenius机制共同控制。所得液氧喷雾分布和其它流场参数与试车数据吻合,所提方法可应用于其它火箭发动机内流场的数值仿真,为发动机设计提供基础数据。
Based on the discrete particle model, the three-particle full-size numerical simulation of two-phase turbulent flow in a rocket engine was carried out by using in-cell particle source method. The liquid oxygen atomized droplets were analyzed by Rosin-Rammler distribution model. The mass average diameter was calculated by coaxial DC nozzle atomization model. The liquid-oxygen high pressure evaporation process was considered. The combustion rate was controlled by the turbulent pulsation mechanism and the Arrhenius mechanism. The obtained liquid oxygen spray distribution and other flow field parameters agree well with the test data, and the proposed method can be applied to the numerical simulation of the flow field in other rocket engines to provide the basic data for engine design.