首页 | 本学科首页   官方微博 | 高级检索  
     检索      

数值模拟纵向隔热屏加力室热态流场
引用本文:黄海明,赵坚行.数值模拟纵向隔热屏加力室热态流场[J].航空动力学报,2007,22(11):1826-1832.
作者姓名:黄海明  赵坚行
作者单位:南京航空航天大学,能源与动力学院,南京,210016;南京航空航天大学,能源与动力学院,南京,210016
摘    要:数值研究纵向隔热屏加力燃烧室的在三维贴体坐标系下燃烧整体流场,所用的数学模型有:k-ε模型、EBU-Arrehenius和二阶矩紊流燃烧模型及六通量模型等.数值分析两种不同几何形状、进口气流参数分布及紊流燃烧模型等对加力室内各气流参数、隔热屏和加力室筒体壁面温度分布的影响,计算结果与试验数据比较表明:不同几何形状对加力室紊流燃烧流场的影响要比进口气流参数分布大些,二阶矩模型更适用模拟紊流燃烧流动. 

关 键 词:航空、航天推进系统  加力燃烧室  纵向隔热屏  贴体坐标  三维紊流燃烧
文章编号:1000-8055(2007)11-1826-07
收稿时间:2006/11/16 0:00:00
修稿时间:2006年11月16

Numerical simulation of three-dimensional heat flows for longitudinal heat shield afterburner
HUANG Hai-ming and ZHAO Jian-xing.Numerical simulation of three-dimensional heat flows for longitudinal heat shield afterburner[J].Journal of Aerospace Power,2007,22(11):1826-1832.
Authors:HUANG Hai-ming and ZHAO Jian-xing
Institution:College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Abstract:Athree-dimensional turbulent combustion flow field of longitudinal heat shield afterburner was numerically investigated in a body-fitted coordinate system.The k-ε model,EBU-Arrhenius and Second-moment turbulent combustion model,as well as six flux model were used.The influences of two different afterburners,inlet gas parameter distributions and turbulent combustion models on afterburner flow fields and wall temperature profiles were calculated.By comparing the experiment results with the calculated results,it shows that:the effect of different geometric afterburners on turbulent combustion flows was more than inlet gas parameter distributions,and Second-moment combustion model was more suitable for simulating the turbulent reacting flow. 
Keywords:aerospace propulsion system  afterburner  longitudinal heat shield  body-fitted coordinate  turbulent reacting flow
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号