固体火箭发动机喷管扩张段粒子冲刷流场分析  

Particle erosion flow field analysis on nozzle divergent section of SRM

作　　者：苗志文 甘晓松[1] 许团委[1] 晁侃[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2017年第5期562-568,共7页Journal of Solid Rocket Technology

摘　　要：某翼柱形药柱固体火箭发动机喷管扩张段出口部位在试验后出现了与药柱翼槽位置相对应的冲刷痕迹,为了研究Al2O3粒子对喷管扩张段的冲刷规律,对喷管型面改进提供依据,对比了不同湍流模型、颗粒轨道模型对形成冲刷痕迹的影响,分析了发动机喷管扩张段两相流场特征,确定了形成冲刷痕迹的粒径范围,判断了冲刷痕迹的形成时间,提出了喷管型面改进方案。结果表明,喷管扩张段的冲刷痕迹形成于发动机工作的15 s时刻之前,主要由药柱后翼燃烧产物中颗粒粒径分布为10~16μm区间的粒子造成,改进后的喷管型面可有效降低粒子对喷管扩张段的冲刷。Particle erosion marks related to grain fin slots were observed on nozzle divergent section of a finocyl grain SRM after experiments.The main purpose of this research is to investigate the law of particle erosion at the nozzle divergent section and improve the nozzle profile.Effects of turbulence models and particle tracking models on particle erosion were compared.The features of Two-phase flow at the nozzle divergent section were analyzed.The diameter of particles that are relevant to erosion marks was estimated.The time interval of particle erosion was determined.Furthermore,the improved solution of nozzle profile was proposed.The results shows that the particle erosion marks on nozzle divergent section appear after 15 s＇ working process of the SRM.They were mainly caused by the particles among aft-fin combustion products ranging from 10 μm to 16 μm.The improved nozzle profile could decrease the particle erosion effectively.

关 键 词：固体火箭发动机 翼柱形药柱 粒子冲刷 喷管扩张段 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]