固体火箭技术Issue(4)：487-491,5.DOI:10.7673/j.issn.1006-2793.2015.04.007
当量比对超声速燃烧室性能影响的数值研究
Numerical study on the effects of the equivalence ratio on the performance of supersonic combustor
王宏宇 1高峰 1李旭昌 1张涵1
作者信息
- 1. 空军工程大学 防空反导学院，西安 710051
- 折叠
摘要
Abstract
The flow field in the supersonic combustor with strut/ cavity configuration was numerically calculated by using the Euler Lagrange method at Mach 2.The characteristics of the flow field in combustion were analyzed by changing the equivalence ratio and the quantitative performance of the combustor was got.The results show that the effect of combustion back pressure on flow up⁃stream becomes higher with the equivalence ratio increasing,resulting in an expansion of the flow separation and a larger subsonic combustion region.The strut/ cavity configuration makes the flow into two parts downstream the cavity: supersonic flow and subsonic flow.The supersonic combustion region becomes smaller,but the subsonic combustion region becomes larger with the equivalence ra⁃tio increasing,enhancing the mixture efficiency and full combustion.The total pressure coefficient and the momentum increase largely but the combustion efficiency and specific impulse becomes smaller with the equivalence ratio increasing.关键词
超声速燃烧室/当量比/支板凹腔组合/总压恢复系数/燃烧效率/比冲量Key words
supersonic combustor/equivalence ratio/strut/ cavity configuration/total pressure coefficient/combustion efficien-cy/specific impulse分类
航空航天引用本文复制引用
王宏宇,高峰,李旭昌,张涵..当量比对超声速燃烧室性能影响的数值研究[J].固体火箭技术,2015,(4):487-491,5.
