超燃燃烧室支板喷注器燃料掺混优化数值分析  

Numerical Optimization Analysis of Fuel-air Mixing for a Supersonic Combustor with Strut Injector

作　　者：王旭东[1] 高峰[1] 王应洋 张涵[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《弹箭与制导学报》2016年第1期93-98,共6页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金资助

摘　　要：为分析喷孔对带交错支板/凹腔组合结构燃烧室性能的影响,运用数值模拟的方法研究了单个喷孔和多个喷孔与支板的相对位置对燃料掺混效率的影响,并探讨了流场在不同喷射角度下的变化情况。研究发现:喷孔正对下斜支板更有利于燃料向燃烧室中心区域扩散,提高混合效率,此结论同样适用于多喷孔喷射;喷射角越接近90°,越有利于提高燃料的穿透深度,同时远场穿透能力随之增强。但喷射角度越大,总压损失越大。To analyze effects of injectors on characteristics of supersonic combustor with staggered rear strut and cavity,numerical simulation was carried out to investigate influence of different injection positions for single and multiple injectors on mixing efficiency of fuel. At last,the effects of the injectors on flow filed with different injection angles were explored. The findings of the study are as follows,the injector which facing directly to the declivity of the strut has better effect on spreading of fuel and mixing efficiency,the conclusion also applies to multiple injectors. With injection angle approaching 90°,the penetration depth and distance of the fuel increase. With increasing of injection angle,total pressure loss also increases.

关 键 词：超燃燃烧室 支板 喷孔位置 喷射角度 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]