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.
出处
《热能动力工程》
CAS
CSCD
北大核心
2016年第10期25-31,123-124,共7页
Journal of Engineering for Thermal Energy and Power
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
film-cooling
thermal shock load
structured grid
block topology
first layer thickness
temperature field
