摘要
设计了两种孔间距比的雪花型层板冷却结构 ,采用有限体积法求解三维可压缩的 N- S方程对其内部流动和换热进行了数值模拟。网格划分采用非结构化网格 ,湍流模型为 Realizable k-ε双方程模型 ,近壁处湍流采用壁面函数法处理 ,采用 SIMPLE算法求解速度与压力的耦合。计算获得了这两种冷却结构内部各气流参数的三维分布及流动阻力特性和换热特性。结果表明 ,层板内部的流场结构十分复杂 ,射流冲击后在扰流柱前反卷形成驻涡 ,呈雪花形分布的扰流柱阵列的存在对气流起到了较好的分流和引导作用 ,使气流在冷却通道内分布更为均匀 ,改善了层板换热的均匀性。数值计算对于改进层板内部结构优化设计有着重要的实际应用价值。
Two snowflake lamilloy models with different hole spacing and diameter ratio was designed and numerical simulation was conducted to study the internal flow field and heat transfer of the two configuration. A finite volume method with unstructured meshes was used to solve the threee dimensional compressible Navier Stokes equations. The Realizable turbulence model was used and standard wall function was used for near wall treatment. The coupling of velocity and pressure were performed using the SIMPLE algorithm. The flow resistance and heat transfer characteristics of the two models were obtained. The numerical results show that the flow fields of the snowflake laminate plates are very complex. A stagnated vortex is formed in the front of pin elements. The existence of the snowflake pin fin leads more uniform distribution of the flow in internal passage and then improve the heat transfer characteristics. The numerical method plays an important role in lamilloy design.
出处
《热科学与技术》
CAS
CSCD
2004年第1期55-59,共5页
Journal of Thermal Science and Technology
基金
国家"973"基金资助项目 (JC2 0 0 0 0 50 50 0 50 1)
西北工业大学博士论文创新基金资助项目 (CX2 0 0 3 15)
关键词
航天推进系统
冷却系统
层板
数值模拟
流阻特性
扰流柱
aerospace propulsion system
coolant system
lamilloy
numerical simulation
flow resistance
pin fin
