超燃燃烧室肋片/凹腔组合结构研究  

Study on Pylon/cavity Combination in a Supersonic Combustion

作　　者：杨文佳 高峰[1] 王应洋 马新鹏 YANG Wenjia;GAO Feng;WANG Yingyang;MA Xinpeng(Air Force Engineering University, Xi’an 710051, China)

机构地区：[1]空军工程大学

出　　处：《弹箭与制导学报》2019年第1期113-118,124,共7页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为进一步了解超燃冲压发动机内流特性,优化燃烧室流场,文中运用数值模拟方法在冷流条件下对比分析了肋片/凹腔结构不同组合距离对流场的影响。研究发现:肋片结构的加入能较大提升射流穿透深度,增强掺混,同时不会带来较大总压损失;组合距离越小,对燃料的掺混扩散更有利,凹腔的稳焰能力也更强,却带来更大的总压损失;综合考虑,肋片与凹腔组合距离为6d时,燃料穿透深度、混合效率更好,总压损失也相对较小。The numerical simulation has been carried out to investigate the cold flow characteristics for mixing efficiency and flame stability of the composite structure of pylon and cavity in the supersonic combustion. The different combination distance of pylon / cavity structure has been comparative analyzed and investigated. It is noted that the pylon can increase the penetration depth of the jet and mixing efficiency, and it won* t lead to a higher total pressure loss. The decrease of combination distance enhances the blending and improves the flame stability, but also increase the total pressure loss. Moreover, the distance between pylon and injector of 6d is recommended regarding high mixing efficiency and less total pressure loss.

关 键 词：超燃燃烧室 肋片 凹腔 数值模拟 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]