气膜冷却叶片热冲击分析网格生成技术  

Grid Generation Technology for the Analysis of Air-film Cooling Vane subjected to Thermal Shock Load

作　　者：关鹏[1] 艾延廷[1] 石小江 包天南 

机构地区：[1]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,辽宁沈阳110136 [2]中航工业燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703

出　　处：《热能动力工程》2016年第10期25-31,123-124,共7页Journal of Engineering for Thermal Energy and Power

摘　　要：针对涡喷2型航空发动机涡轮的导向叶片,建立气膜冷却叶片几何模型,利用分块拓扑法在不切割几何体的情况下生成高质量的结构化网格,并根据湍流模型的要求对近壁面网格尺寸进行优化。根据该型发动机地面实验数据,以发动机技术状态参数为依据定义边界条件,对生成的网格进行稳态及瞬态数值模拟。研究表明:一体化网格生成可以减小系统误差,提高计算精度;第一层网格厚度对网格质量影响较大,应综合考虑y^+的精确值进行设定;数值模拟结果同实验数据基本吻合,此网格生成方法具有工程应用价值。Mesh division is the basis for thermal shock numerical simulation of film cooling blade and turbine cascade. Because of the complicated structure of film cooling blade as well as strict requirements on the first layer thickness for numerical heat transfer simulation,grid generation scheme is the key of this issue. In this paper,the geometry of Gas Turbine Ⅱ nozzle guide vane was used,and structured grids of high quality were generated using the method of block topology without cutting geometry. The near wall grid size was optimized according to the requirement of turbulence model. Based on the ground experimental data,boundary conditions were defined and the generated grids were tested in both steady-state and transient simulations. The results show that integration of grid generation can reduce the system error and improve the calculation accuracy. The first layer has a greater influence on the quality of grid,so it should be determined by considering the y+value. The simulation results using this structured grid agree well with the experimental data,indicating the engineering application value of the grid generation technology presented in this paper.

关 键 词：气膜冷却叶片 热冲击 结构化网格 分块拓扑 第一层网格厚度 温度场 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]