固体火箭发动机喷管喉部凝相颗粒粒度分布实验  

Experimental Investigation on the Condensed Particles Size Distribution at SRM Nozzle Throat

作　　者：张胜敏[1] 胡春波[1] 夏盛勇[1] 李佳明[1] 

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《推进技术》2012年第2期245-248,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金(50976095)

摘　　要：设计了一种新的收集固体火箭发动机喷管凝相颗粒的实验装置,针对典型的HTPB复合推进剂,开展了喷管喉部凝相颗粒的收集实验和粒度分析,研究了燃烧室压强和收敛角度对喷管喉部颗粒粒度分布的影响规律。研究结果表明,喷管喉部的凝相颗粒在0.27～50μm之间都有颗粒存在,凝相颗粒主要集中在0.3～15μm之间,粒径大于15μm的颗粒较少;燃烧室压强对颗粒粒径有较大影响,随着燃烧室压强的升高,凝相颗粒粒径变小,粒度分布更为集中;燃烧室压强相同的条件下,收敛角度对喷管喉部的凝相颗粒粒度分布影响较小。A new device was designed to collect the condensed particles at the nozzle throat of the SRM. The typical HT- PB composite propellant containing 17% aluminum was experimentally investigated under different condition. Collection experiments and particle size analysis were performed so as to investigate the effects of chamber pressure and concentration degree on particle size distribution. The experimental resuhs show that the range of particle size is from 0.27μm up to about 50μm. The majority of particle size is from 0.3μm to 15μm. The results indicate that the particle size distribution is primarily dictated by the chamber pressure. The particle size was decreased with the increase of the chamber pressure while time the diameter distribution is concentrated. It is found that with the increase of the concentration degree, the particle diameter is slightly changed.

关 键 词：固体火箭发动机 喷管喉部 凝相颗粒 粒子收集 粒度分布 

分 类 号：V512.3[航空宇航科学与技术—航空宇航推进理论与工程]