摘要
为了在不增加燃烧室整体阻塞比的情况下提升流向涡强度,设计了一种尾部有压缩角的交替尾缘支板,并对不同结构支板喷注器的喷流流场和燃烧场进行了三维数值模拟。研究发现:支板尾部的压缩角对喷流流场产生了一定影响,并增强了交替尾缘结构诱导产生的流向涡强度;在尾部增加压缩角虽然带来了一定的总压损失,但是有效地提高了燃料的混合效率和扩散范围;从燃烧性能上看,添加尾部压缩角对燃烧室的燃烧范围和燃烧效率均有提升。
In order to increase the strength of streamwise vortices without increasing the choke ratio of combustor, this paper designs an alternating-wedge strut with a compression angle at the tail, Characteristics of non-reacting flow field and reacting flow field of different strut were investigated numerically. The results of numerical simulation show that: the compression angle at the tail affects the flow filed of injection and enhance the strength of streamwise vortices;Adding the compression angle at the tail results in more total pressure loss, but increases fuel mixing efficiency and diffusion range;From the perspective of combustion performance, the addition of compression angle significantly improves the combustion range and combustion efficiency of the combustor.
作者
张喆
席文雄
金星
ZHANG Zhe;XI Wenxiong;JIN Xing(State Key Laboratory of Laser Propulsion and Application,Space Engineering University,Beijing 101416,China)
出处
《弹箭与制导学报》
北大核心
2019年第5期39-45,49,共8页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金(51606220)资助。
关键词
压缩角
支板喷注器
交替尾缘结构
混合
燃烧效率
compression angle
strut injector
alternating-wedge structure
mixing
combustion efficiency
