摘要
为进一步研究不同肋片构型对后方射流的影响规律,运用数值模拟方法,研究了统一特征尺寸下不带前引导面与带前引导面等10种不同构型肋片流场特性差异。研究发现,肋片后低动压喷射的总压损失主要由壁面与横向射流产生,与传统横向喷流算例相比,带Pylon A和Pylon D的算例总压损失有所减小;肋片后缘面越大能提供的低压区越大,后缘面过大燃料组分扩散过早,羽流质量中心高度未必越大,无论后缘面前倾或后倾流场特性无明显改善;前引导面对掺混特性的影响效果大于后缘面对掺混特性的影响效果,Pylon D、Pylon I及Pylon J构型的肋片最具进一步研究价值。
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 smaller 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 efficiency. 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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2016年第1期28-35,共8页
Journal of Solid Rocket Technology
基金
航空科学基金(20130196004)
关键词
超燃燃烧
肋片
掺混增强
数值模拟
supersonic combustion
pylon
mixing enhancement
numerical simulation
