辅助动力装置环形回流燃烧室数值研究  

Numerical study of auxiliary power unit annular backflow combustor

作　　者：林志勇[1] 颜应文[1] 李井华[1] 朱嘉伟[1] 陈利强[2] 孔祖开[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司金城南京机电液压工程研究中心,南京211106

出　　处：《航空动力学报》2012年第8期1726-1733,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(50906040);南京航空航天大学基本科研业务费专项科研项目(NZ2012107)

摘　　要：利用Fluent软件计算辅助动力装置(auxiliary power unit,简称APU)环形回流燃烧室三维两相喷雾燃烧流场,研究不同进口温度和油气比对两相喷雾燃烧流场的影响,采用标准k-ε模型模拟湍流黏性,离散相模型(DPM)追踪油珠运动轨迹,燃烧模型采用非预混平衡化学反应模型.计算结果表明:随着进口温度和油气比的增加,燃烧室出口温度相应增加,但温度分布规律基本保持不变;计算结果与试验测量结果比较吻合,说明采用的数学模型和计算方法可用于预估实际APU回流燃烧室三维两相喷雾燃烧流场.The influences of different inlet conditions （including inlet temperature and inlet fuel air ratio） on two phase spray combustion flow of auxiliary power unit （APU） com- bustor were studied by using Fluent software. Standard k-ε model was applied to simulate the turbulent viscosity. The fuel droplet trajectories were modeled in Lagrangian frame of reference by using discrete phase model （DPM）. Non-premixed combustion model was used to model turbulence-chemistry interaction. The results reveal that the outlet temperature raise with the increase of inlet temperature and fuel-air ratio, but distribution of temperature is similar. The numerical data agree well with experimental data, which show that the numerical model and method can be used to predict two phase spray combustion flow of APU.

关 键 词：辅助动力装置 环形回流燃烧室 两相喷雾燃烧 离散相模型 非预混平衡化学反应 

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]