固体火箭发动机Al_(2)O_(3)颗粒喷管沉积特性研究

Study on Deposition Characteristics of Al_(2)O_(3) Particle Nozzles in Solid Rocket Motors

论文以潜入式喷管固体火箭发动机为研究对象,基于CFD软件OpenFOAM,采用欧拉–拉格朗日两相流模型,选用颗粒沉积统计方法,分析了不同颗粒粒径、颗粒初速度和颗粒质量流量对发动机喷管沉积的影响。研究结果表明,对于含潜入式喷管的固体火箭发动机,颗粒主要在背壁区域发生沉积,气流漩涡对颗粒运动轨迹的影响是背壁区域沉积量大的主要因素。背壁区域和凸缘段沉积率随颗粒平均直径增大而减小,所有部位的总沉积率受颗粒初速度影响不大,各部位沉积率随颗粒质量流量增大而增大,背壁面沉积率增长尤为明显。

In this paper,the solid rocket motor with submerged nozzle is used as the research object.Based on the CFD software OpenFOAM,the Euler-Lagrangian two-phase flow model and the mechanism of mechanical deposition are used.The particle deposition statistical method was used to analyze the effects of different particle sizes,initial particle velocities,and particle mass flow rates on engine nozzle deposition.The research results indicate that for solid rocket engines with submerged nozzles,particles mainly deposit in the back wall area,and the influence of airflow vortices on particle trajectory is the main factor for the large deposition amount in the back wall area.The sedimentation rate of the back wall area and flange section decreases with the increase of the average particle diameter,and the total sedimentation rate of all parts is not significantly affected by the initial particle velocity.The sedimentation rate of each part increases with the increase of particle mass flow rate,and the growth of sedimentation rate on the back wall surface is particularly significant.