超燃燃烧室肋片/凹腔结构组合数值研究  

Numerical 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,西安710051

出　　处：《弹箭与制导学报》2019年第5期89-94,共6页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为进一步优化燃烧室流场,运用数值模拟方法在冷流条件下对不同凹腔长深比和后壁面倾角对肋片/凹腔结构组合燃烧室流场的影响进行研究。结果表明:增大凹腔长深比和减小凹腔后壁面倾角能较好提高射流穿透深度和掺混效率,但造成较大总压损失,且倾角越小倾角变化对总压损失的影响越明显;综合考虑,采用长深比为3、后壁面倾角为45°的凹腔与肋片进行结构组合能较好增大燃料穿透深度,促进掺混,且不明显增大总压损失。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 length-to-depth(L/D) and aft ramp angle(α) of the cavity structure have been comparative analyzed and investigated. It is noted that larger L/D are helpful in increasing the penetration depth of the jet and mixing efficiency, but also lead to a higher total pressure loss;The decrease of cavity aft ramp angle increase the penetration depth of the jet and total pressure loss, and the smaller the aft ramp angle is, the more obvious the influence of angle change on total pressure loss is. Moreover, cavity with the length-to-depth of 3 and aft ramp angle of 45° 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]