国防科技大学学报2012，Vol.34Issue(4)：13-17,5.
小推力液体火箭发动机燃烧与传热数值仿真研究
A numerical study of combustion and heat transfer in small thrust liquid rocket engine
摘要
Abstract
By introducing VOF model to simulate the cooling liquid film in small thrust liquid rocket engine, numerical method was performed to calculate and evaluate the effects of the expansion size on combustion efficiency and heat transfer in the chamber. Comparison shows the calculation is reasonable. It has shown that as the dimensionless expansion height H* increases from 0.111 to 0. 222, combustion efficiency and specific impulse increase by 0.35 % and 0.5s. However, the dimensionless expansion length L * plays a less significant role in the process. As it increases from 1.389 to 1.944, combustion efficiency and specific impulse decrease by 0. 11 % and 0.3s respectively. It is evident that the heat transfer characteristics of thrust chamber keep stable in the variation of H * or L* . This shows in expansion thrust chamber, the main reason for combustion efficiency loss should be that gaseous MMH adjacent side wall cannot mix with gaseous oxidant efficiently.关键词
小推力液体火箭发动机/燃烧/数值模拟/扩张型推力室/VOF模型Key words
small thrust liquid rocket engine/ combustion/ numerical simulation expansion thrust chamber/ VOF分类
航空航天引用本文复制引用
林庆国,周进..小推力液体火箭发动机燃烧与传热数值仿真研究[J].国防科技大学学报,2012,34(4):13-17,5.基金项目
国家部委基金资助项目 （）
