摘要
本文提出了一种适用于多级压气机的快速三维数值气动设计方法,该方法的核心是应用一种快速网格生成技术和NS方程求解器之间不断的相互迭代,最终得到各叶片排的三维叶片造型。首先给定流量,压比和压气机子午通道的几何形状。在初始设计阶段通过计算得到各叶片排沿叶高周向平均的进出口气流角分布,并把其作为计算的目标参数。然后通过网格生成和NS求解之间的迭代,不断调整目标参数,直到计算收敛。应用本方法设计了一台具有三个重复级的实验用轴流低速压气机。
The present paper presents a rapid numerical method for 3D aerodynamic design of multistage compressors which is based on the iterative calculations by successively using a grid generation method and a N.S. solver. At beginning the flow rate, the pressure ratio and the geometry of meridian pattern were given. The span-height distributions of inlet and exit pitch-wise- averaged flow angles (or blade circulation) of the blade channel were obtained by the preliminary calculations. They are served to be the target parameters of the present calculation. Successively using a grid generation method and a N.S. solver, a 3D blade configuration can be obtained. As an example a low-speed compressor with three identical stages is shown.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2003年第4期583-585,共3页
Journal of Engineering Thermophysics
基金
国家重点研究规划项目(No.G1999022306)
中国科学院知识创新项目(No.KGCX2-301)
关键词
叶轮机械设计
turbomachinery design
