基于曲线坐标系浸没边界方法的折流燃烧室模拟  

Simulation of Slinger Combustor Based on Curvilinear Coordinate System Immersed Boundary Method

作　　者：王煜栋 王方[1,2,3] 甘甜 金捷[1,2,3] WANG Yu-dong;WANG Fang;GAN Tian;JIN Jie(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Jiangxi Research Institute,Beihang University,Nanchang 330096,China;Chengdu Innovation Research Institute on Aircraft Power of Beihang University,Chengdu 611930,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学江西研究院,江西南昌330096 [3]北京航空航天大学成都航空动力创新研究院,四川成都611930

出　　处：《推进技术》2023年第5期118-130,共13页Journal of Propulsion Technology

基　　金：国家科技重大专项(2017-Ⅰ-0004-0005);国家自然科学基金(91741125)

摘　　要：航空发动机折流燃烧室几何结构复杂,其高保真数值模拟需要高效的网格与边界条件处理方法。采用曲线坐标系隐式浸没边界方法结合大涡模拟-概率密度函数输运方程湍流燃烧模型开发自研软件,并实现WP11中折流燃烧室的高保真模拟。流动模拟中准确解析了该燃烧室中的三股主要气流,且三股气流分别约占进口流量的75%,12.5%和12.5%。两相燃烧模拟中针对拉格朗日框架下的液滴运动和欧拉框架下的湍流燃烧采用不同网格标记,模拟得到的出口径向温度分布规律与实验一致,平均相对误差为17.95%,表明基于本方法开发的自研软件能准确模拟折流燃烧室中的两相湍流燃烧现象。The high-fidelity numerical simulation of the complex geometry of an aero-engine slinger com⁃bustor requires efficient meshing and boundary condition processing methods.We use the implicitly immersed boundary method in curvilinear coordinate system combined with large-eddy simulation and transported probabil⁃ity density function turbulent combustion model to develop the self-developed software and realize the high fideli⁃ty simulation of the slinger combustor in WP11.The three main flows in the combustor are accurately resolved in the flow simulation,and the three flows account for about 75%,12.5%and 12.5%of the inlet flow,respectively.The two-phase combustion simulation uses different grid labels for droplet motion in the Lagrangian frame and turbulent combustion in the Eulerian frame,and the simulated outlet radial temperature distribution pattern is consistent with the experiment with an average relative error of 17.95%,indicating that the self-developed soft⁃ware based on this method can accurately simulate the two-phase turbulent combustion phenomenon in the sling⁃er combustor.

关 键 词：数值模拟 浸没边界方法 大涡模拟 概率密度函数输运方程 湍流燃烧模型 折流燃烧室 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]