基于模型燃烧室的回火过程数值模拟和机理  

Numerical simulation and mechanism of flame flashback process based on model combustor

作　　者：杨琨 田泽民 刘重阳 齐东东 颜应文[1] YANG Kun;TIAN Zemin;LIU Chongyang;QI Dongdong;YAN Yingwen(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《航空动力学报》2024年第11期277-290,共14页Journal of Aerospace Power

基　　金：中国航发涡轮院稳定支持项目(GJCZ-2020-0039)。

摘　　要：以旋流预混模型燃烧室为对象,基于试验手段获得了不同压力下航空煤油预混火焰的回火发生边界条件及其动态过程。以此为基础,基于雷诺平均方法,利用realizable k-ε及小火焰生成模型(FGM),数值地复现了回火发生的临界状态。数值计算获得的回火压力边界与试验结果相比,误差不超过10%。利用大涡模拟方法,精细化再现了典型工况下回火的发生和发展过程。分析表明,下游压力增加引起预混通道出口附近压力和密度脉动耦合变化,产生具有负速度区的逆向涡旋。下游压力持续增大使逆向涡旋增大,将预混通道外的热焰带入通道内,诱发回火。进一步,在斜压梯度的作用下,预混通道内的火焰不断向上游传播。The boundary conditions and propagation process of flame flashback were experimentally obtained for aviation kerosene at different pressures in a premixed swirl model combustor.The reliable k-εmodel of Reynolds average Navier-Stokes method,coupled with flamelet generated method(FGM),was applied to numerically capture the flame flashback.It was shown that the simulated critical pressure conditions were within 10%errors compared with the experimental results.Then the large eddy simulation method was used to reproduce the flame flashback process in detail.The analysis showed that the combination of fluctuations of pressure and density in the region near the exit of premix tube caused by increase of downstream pressure yielded reverse eddy with minus speed.As the reversed eddy was enlarged with the increase in downstream pressure,the hot flame outside the exit of premix tube was brought into the tube,which induced flame flashback.Then the flame in the premix tube propagated upstream due to the influence of baroclinic pressure.

关 键 词：旋流预混燃烧室 回火 数值模拟 贫燃预混 液态燃料 

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]