旋流驻涡燃烧室预混燃烧流动特性数值分析  

Numerical Study on Flow Characteristics of Premixed Combustion of Swirling Trapped Vortex Combustor

作　　者：要晋龙 徐青[1] 鄢平华 孙海俊[3] Yao Jinlong;Xu Qing;Yan Pinghua;Sun Haijun(College of Civil and Architecture,East China Jiaotong University,Nanchang 330013,China;College of Artificial Intelligence,Jiangxi College of Application Science and Technology,Nanchang 330100,China;College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]华东交通大学土木建筑学院,南昌330013 [2]江西应用科技学院人工智能学院,南昌330100 [3]南昌航空大学飞行器工程学院,南昌330063

出　　处：《航空兵器》2020年第5期63-68,共6页Aero Weaponry

基　　金：国家自然科学基金项目(51741902);江西省教育厅基金项目(GJJ180543)。

摘　　要：旋流驻涡燃烧室采用凹腔与旋流组合方式进行稳焰,为探究预混燃烧条件下的旋流驻涡燃烧室燃烧流动特性,本文采用数值计算方法分析了不同旋流数对燃烧室热态流场、燃烧效率、总压损失等的影响规律。研究结果表明:不同旋流数时,凹腔内均形成单涡结构,在旋流数S=0.1时,旋涡中心基本位于凹腔几何中心;整体而言,总压恢复系数σ随旋流数S先升后降再升,在S=0.1时,总压恢复系数最大,σmax=0.851;燃烧效率随旋流数变化波动较大,在S=0.1时,燃烧效率较高,ηc=0.966,且可在距离凹腔更短的下游达到最高的燃烧效率,有望缩短燃烧室长度,提高发动机推重比。A swirling trapped vortex combustor is designed to stabilize flame with the combination of cavity and rational flow.In order to investigate the combustion flow characteristics of swirling trapped vortex combustor under the condition of premixed combustion,the effects of different swirl numbers on the combustor hot flow field,combustion efficiency and total pressure loss at different swirling conditions are analyzed by numerical method.The results show that single vortex is formed in the cavity at all cases.Meanwhile,while swirl number S=0.1,the vortex core position is located at the vicinity of cavity geometric center.Overall,the total pressure recovery coefficientσis up-down-up along with the growth of the swirl number,and the maximum pressure recovery coefficientσmax=0.851 when S=0.1.The combustion efficiency fluctuates along the swirl number,which is higher(ηc=0.966)than other cases when the swirl number S=0.1,and the highest combustion efficiency can be achieved at downstream closer to the cavity,which is expected to shorten the length of the combustor and to improve the engine thrust-weight ratio.

关 键 词：冲压发动机 驻涡燃烧室 旋流 数值模拟 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V235[航空宇航科学与技术—航空宇航推进理论与工程]