潜入喷管背壁区熔渣沉积的机理分析与数值模拟  

Mechanism investigation and numerical simulation of slag deposition for submerged nozzle

作　　者：魏超 侯晓 

机构地区：[1]中国航天科技集团四院,陕西西安710025

出　　处：《航空动力学报》2006年第6期1109-1115,共7页Journal of Aerospace Power

摘　　要：为了探求固体火箭发动机潜入喷管背壁区中熔渣沉积的机理和预估方法,采用欧拉-拉格朗日法模拟两相内流场,采用随机轨道模型跟踪离散相轨迹,确定了燃烧室中粒子的直径分布和两种熔渣捕获判据,分析了不同壁面恢复系数对熔渣沉积计算的影响,计算得到的熔渣最小占Al2O3总生成量的0.201%,最大占到0.287%。与实验数据对比证明该预估方法是准确可靠的。In order to explore the mechanism and the model of slag generation in solid propellant rocket motor, the two phase flowfield has been simulated using a combined Eulerian-Lagrangian analysis. The motion of the particulate phase was tracked with a stochastic model. The droplet size distribution in the chamber and the two captive rules were considered. Finally, the influence of different coefficients of restitution on slag calculation was investigated. The calculated result shows that the lowest slag weight is 0. 201% and the highest slag weight is 0. 287% of the total weight of Al2O3. The results are accurate and credible compared to the experimental data.

关 键 词：航空 航天推进系统 固体推进剂火箭发动机 两相流场 潜入喷管 熔渣沉积 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]