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含有氧化铝粒子的两相流是固体火箭发动机喷管流场的重要特征.在有限体积方法框架下,采用基于热增量试验数据的粒子壁面反弹模型以及基于粒子轨道的单元内颗粒源(PSIC,Particle Source in Cell)两相流耦合算法,对喷管内两相流流场及粒子撞击产生的壁面热增量进行了计算和分析,研究了氧化铝粒子尺寸对粒子轨道分布和喷管壁面热增量分布的影响规律.研究结果表明:喷管扩张段内粒子稀疏区域范围随粒子直径增加而增大;粒子热增量只分布于喷管收缩段内,粒子直径越大,产生的壁面热增量越强.
Two-phase flow with alumina particles is an important feature of the flow field of a solid rocket motor nozzle.Under the framework of the finite volume method, a particle wall rebound model based on thermal increment test data and a particle orbital-based intraparticle particle source (PSIC , Particle Source in Cell) is used to calculate and analyze the flow field of two-phase flow in the nozzle and the wall heat increment caused by particle impact. The effect of alumina particle size on the particle orbit distribution and nozzle wall heat The results show that the range of particle sparse area increases with the increase of particle diameter in the expanding section of the nozzle, and the thermal increment of particles is only distributed in the contraction section of the nozzle. The larger the particle diameter, the larger the wall heat Incremental increase.