摘要
为了获得涡轮工作叶片内冷通道的换热特性,采用非结构化网格及standardk-ε紊流模型,求解三维N-S方程,对带60°肋和气膜孔出流的旋转矩形通道内的三维流场进行了数值模拟,近壁面采用增强壁面函数处理。气动参数为:通道入口雷诺数60 000,罗斯贝数0.22,气膜孔总出流比0.22。重点分析了静止通道和不同旋转方向的旋转通道的换热系数分布。计算结果表明,静止通道由于肋的存在使换热显著增强,不同的旋转方向对换热强化的效果不同,顺时针旋转时的增强效果要高于逆时针旋转时的增强效果。
Numerical simulation was conducted to investigate heat transfer in rectangular channel with both rib-roughened wall and film hole suctions at Reynolds number 60 000, rotation number 0.22, suction ratio of 0.22. A finite volume method with unstructured meshes was used to solve the three dimensions compressible Navier-Stokes equations. The standard k - ε model was used and the enhanced wall function was utilized for near wall treatment. The focus of investigation is heat transfer coefficient and heat transfer enhanced factor distribution. Heat transfer is enhanced duo to the ribs. The effect of rotation, especially clockwise tunnel, has pronounced influence on heat transfer.
出处
《汽轮机技术》
北大核心
2008年第4期273-275,共3页
Turbine Technology
关键词
航空发动机
涡轮工作叶片
肋
气膜孔
换热
数值仿真
aircraft engine
turbine blade
rib
film hole heat transfer
numerical simulation
