固体火箭技术2011，Vol.34Issue(4)：453-456,4.
双脉冲发动机燃烧室局部烧蚀特性分析
Analysis of local ablation characteristics in combustion chamber of dual-pulse motor
刘亚冰 1王长辉 1刘宇1
作者信息
- 1. 北京航空航天大学宇航学院,北京100191
- 折叠
摘要
Abstract
Aimed at the local ablation enhancement problem in the 1st pulse combustion chamber of a dual-pulse motor, numerical simulation of the two-phase inner flow in two dual-pulse motors with φ203 mm and φ120 mm in caliber respectively was conducted. The vortex movement of gas in the combustion chamber and its two-phase characteristics were analyzed, which were induced by the chamber area sudden expansion. The heat convection intension on the chamber wall was computed by an expirical formula. By comparing the calculation results with the experinental data, it was revealed that the convection enhancement zone was consistent with the local ablation spot well. The chamber wall heat convection in the gas vortex region, especially near the reattachment point, was much higher than in the other chamber wall regions, which caused the local ablation enhancement. In addition, when the propulsion grain had metal involved, a portion of metal-oxide particles in smaller size were carried into the vortex zone and moved to the upstream chamber wall. Those particles may deposit on the chamber wall.关键词
双脉冲固体发动机/燃烧室/内流场/烧蚀Key words
dual-pulse solid rocket motor/combustion chamber/internal flow field/ablation分类
航空航天引用本文复制引用
刘亚冰,王长辉,刘宇..双脉冲发动机燃烧室局部烧蚀特性分析[J].固体火箭技术,2011,34(4):453-456,4.
