固体火箭技术2012，Vol.35Issue(3)：335-338,4.
某双脉冲发动机燃烧室两相流场数值分析
Numerical analysis of two-phase flow in combustion chamber of dual-pulse motor
孙娜 1娄永春 1孙长宏 1沈铁华1
作者信息
- 1. 上海航天动力技术研究所,上海201109
- 折叠
摘要
Abstract
The lengthways erosion of the insulation in the dual-pulse solid rocket motor was uneven after the experimentation, and the pit appeared on the insulation of the forepart of I-pulse-chamber. In order to find out the reason of this phenomenon, the numerical simulation of two-phase flow in the combustion chamber was made with FLUENT. The backward-facing step flow appears in I-pulse-chamber,because of the channel between the I and II chamber of the dual-pulse SRM, which causes the flow separation. From the simulation result,the serious erosion of the insulation in I-pulse-chamber occurs on the place of realtachment and the part of the particles ablation. Therefore,the flow reattachment and the particles ablation are the important causes of the uneven erosion of the insulation in I-pulse-chamber.关键词
双脉冲固体火箭发动机/两相流/燃烧室/数值分析Key words
dual-pulse solid rocket motor/two-phase flow/combustion chamber/numerical simulation分类
航空航天引用本文复制引用
孙娜,娄永春,孙长宏,沈铁华..某双脉冲发动机燃烧室两相流场数值分析[J].固体火箭技术,2012,35(3):335-338,4.
