固体火箭技术2016，Vol.39Issue(1)：28-35,8.DOI:10.7673/j.issn.1006-2793.2016.01.005
超燃燃烧室肋片构型数值研究
Numerical simulation on pylon pattern in a supersonic combustor
摘要
Abstract
The numerical simulation was carried out to investigate the cold flow characteristics of small pylon aided gaseous fuel injection in the supersonic combustion.Ten pylon patterns were evaluated for mixing enhancement,fuel penetration and total pressure loss coefficient.It is noted that total pressure loss is leaded mainly by the wall and jet.Cases with Pylon A and Pylon D can get smal-ler total pressure loss than case with only transverse jet.The bigger rear face of the pylon can provide more low pressure depression which might result in a rapid diffusion of fuel but lower fuel penetration.The angle of rear face has little influence on the mixing effi-ciency.Moreover,the front face has a stronger effect on mixing efficiency than the change of the rear face.The patterns of Pylon D, Pylon I and Pylon J have a further engineering research value.关键词
超燃燃烧/肋片/掺混增强/数值模拟Key words
supersonic combustion/pylon/mixing enhancement/numerical simulation分类
航空航天引用本文复制引用
王应洋,李旭昌,王宏宇,王旭东..超燃燃烧室肋片构型数值研究[J].固体火箭技术,2016,39(1):28-35,8.基金项目
航空科学基金(20130196004)。 （20130196004）
