湍流燃烧模型对双旋流燃烧室喷雾燃烧的影响  

Effects of Turbulent Combustion Models on Spray Combustion Flow of Dual-Stage Swirler Combustor

作　　者：徐榕[1] 李井华[1] 赵坚行[1] 颜应文[1] 刘勇[1] 王锁芳[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2013年第3期375-382,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(50906040);南京航空航天大学基本科研业务费专项科研资助项目资助(NS2010052);江苏省博士后科研资助计划(0901033C)

摘　　要：采用数值模拟与试验测量相结合的方法,研究扩展旋涡破碎模型、扩展二阶矩模型和涡团耗散概念模型等三种湍流燃烧模型对双旋流湍流喷雾燃烧流场的影响。在任意曲线坐标系下数值研究双级轴向旋流器环形燃烧室全流程流场,采用粒子图像测速仪测量燃烧流场气流速度分布,热电偶测量燃烧室出口温度分布。计算结果与验证试验数据比较表明:不同湍流燃烧模型对双旋流湍流喷雾燃烧影响较大,所得的回流区形状、速度、温度场以及出口温度分布等都不太相同,其中扩展二阶矩模型所得的结果与试验值符合最好,更适用于模拟双旋流环形燃烧室湍流喷雾燃烧。The effects of different turbulent combustion models on turbulent swirling two-phase spray combustion flows were investigated numerically and experimentally in the dual-stage swirler combustor.Three turbulent combustion models are the Eddy Break-up-Arrhenius model（EBU-A）,the Second-Order Moment-EBU model（SOM-E） and the Eddy Dissipation Concept model（EDC）.In arbitrary curvilinear coordinates,a multi-zone coupling approach was used for numerical investigations of spray combustion integrated flow fields in an annular combustor with the dual-stage axial swirler.A Particle Imaging Velocimetry（PIV） was employed to measure spray combustion flow fields and the multiple-point thermocouple probes were used for measuring radial profiles of exit gas temperature in the combustor.Comparisons between predicted and experimental data show that the effects of different turbulent combustion models on turbulent swirling spray combustion flows are obvious.The shape of recirculation zone,profiles of velocity and temperature as well as radial profiles of exit gas temperature,are affected with various degree by different turbulent combustion models.Computational results obtained by the SOM-E model are in good agreement with measured experimental data.It is more appropriate than the EBU-A and the EDC combustion model for predicting turbulent swirling spray combustion flows in the dual-stage swirler combustor.

关 键 词：湍流燃烧模型 双级轴向旋流器 环形燃烧室 喷雾燃烧 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]