压气机变形叶片的网格生成及区域分解方法  

Grid Generation and Domain Decomposition Method for Compressor Blade Deformation

作　　者：顾家琦 琚亚平[1] 张楚华[1] GU Jia-Qi;JU Ya-Ping;ZHANG Chu-Hua(School of Energy and Power Engineering,Xi'an,Jiaotong University,Xi'an 710049,Chinn)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049

出　　处：《工程热物理学报》2021年第5期1176-1183,共8页Journal of Engineering Thermophysics

基　　金：国家重点研发计划(No.2016YFB0200901);国家自然科学基金项目(No.51776154);国家科技重大专项项目(No.2017-II-0006-0020);陕西省重点研发计划国际科技合作项目(No.2018KWZ-01)。

摘　　要：针对压气机优化设计和多学科分析对网格自动可靠生成方法的需求,建立了一套集叶片几何参数化建模、多块结构化网格生成、区域自动分解、叶片自由变形于一体的多功能网格生成系统。基于椭圆型微分方程法和O_(4)H型拓扑结构,建立了压气机单叶道流域的三维分块结构化网格生成方法,改进了适合于变形叶片及网格的自由变形方法,自主开发了相应的计算程序,并用NASA Stage35对方法及程序进行了验证。结果表明网格生成质量较好,特别是近壁网格正交性和光滑性俱佳;改进的自由变形方法能够保持网格周期性和轮毂轮盖几何形状;流场计算结果与实验数据吻合良好。研究工作对发展多级高速轴流压气机优化设计和多学科分析系统具有重要参考价值。A multi-functional grid generation system is established which integrates blade geometric parameterization,multi-block structured grid generation,automatic domain decomposition and blade free form deformation,in order to meet the urgent demand of compressor optimal design and multi-disciplinary analysis for the automatic reliable high-quality grid generation.The grid generation method uses a combination of elliptic partial differential equation solver and O_(4) H topology to obtain smooth meshes for the compressor single passage.The free deformation method is revised for the deformed blades and meshes.The developed method and codes are tested with the NASA Stage35.The results shows that the mesh quality of NASA Stage35 is good with improved mesh orthogonality and smoothness at the near solid wall regions.The revised free deformation method maintains both the mesh periodicity and geometry consistence.The flow calculation results are in good agreement with the experimental data.This work is of important reference value for developing design optimization and multidisciplinary analysis system of multi-stage high-speed axial compressor.

关 键 词：轴流压气机 分块结构化网格 叶片变形 区域分解 流场计算 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]