摘要
采用RNGk ε湍流模型,对Capstone公司75kW微型燃气轮机燃烧室火焰筒内气流三维流动过程进行了数值模拟研究.结果表明,燃烧室火焰筒内有3个回流区,其存在将有助于燃料的连续点火和火焰的稳定.由火焰筒后部两排二次空气掺混射流孔射入火焰筒的射流深度不同,且沿流动方向第一排射流孔射流深度大于第二排.此外,火焰筒内气流轴向、径向和切向速度沿火焰筒径向的分布随着气流沿火焰筒轴向的流动逐渐趋于均匀,且其峰值位置朝向火焰筒中心轴方向移动.
Using the RNG k-ε model,numerical investigations on the three-dimensional flow in the micro-gas turbine combustion chamber are carried out.The results indicate that three recirculation zones exist in the combustor liner,which is beneficial to flame ignition and stability.The depths of penetration for the first and second bands of dilution orifices are different,and the air jets from the first band of holes can penetrate into the dilution region further than from the second band.In addition,the axial,radial and tangential velocity profiles along the radius of the combustor liner at different cross sections tend to be uniform and the locations of peak velocity move towards the axis of the combustor liner along the flow direction.
出处
《上海理工大学学报》
CAS
北大核心
2004年第5期425-428,共4页
Journal of University of Shanghai For Science and Technology
基金
上海市重点学科建设资助项目(能源岛关键技术及基地建设)
关键词
微型燃气轮机
燃烧室
湍流
数值模拟
速度场
micro-gas turbine
combustion chamber
turbulence
numerical simulation
velocity field
