大涡模拟航空发动机加力燃烧室内部流场  

Large Eddy Simulation of Flow Field in Aircraft Engine Afterburner

作　　者：张书铭 杨雨 李井华[1] ZHANG Shuming;YANG Yu;LI Jinghua(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

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：《机械制造与自动化》2020年第3期102-104,共3页Machine Building & Automation

摘　　要：为研究航空发动机加力燃烧室内部气流的流动情况,基于LES计算方法,选用动态亚网格湍流模型对燃烧室内非反应流场进行数值研究。模拟结果显示:在中心锥后侧有较大回流区;在空心叶片尾部存在稳定回流区,表明大涡模拟动态亚网格模型能够模拟出加力燃烧室筒体内尺寸较小的涡团及涡团的掺混耗散过程,可较好地展现加力燃烧室实际的流动过程和特性。To study the flow field in the afterburner of the aircraft engine,the dynamic sub-grid-scale turbulence model is used to make a numerical study of the non-reactive flow field in the afterburner.The numerical simulation results show that a large recirculation zone is formed on the back side of the central cone and a stable recirculation zone occurs at the end of the hollow blade.The results show that large eddy dynamic sub-grid-scale turbulence simulation model can be used to simulate the mixing and dissipation process of small vortex in the afterburner cylinder,thus better showing the flow process and characteristics of the actual afterburner.

关 键 词：航空发动机 加力燃烧室 大涡模拟 动态亚网格模型 

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]