含气膜孔涡轮叶片寿命可靠性设计优化中的网格参数化方法  

Mesh parameterization in reliability-based design optimization for the life of turbine blade with film holes

作　　者：雷婧宇[1] 吕震宙[1] 贾贝熙 LEI Jingyu;LYU Zhenzhou;JIA Beixi(School of Aeronautics, Northwestern Polytechnical University, Xi′an 710072, China)

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《国防科技大学学报》2022年第2期55-63,共9页Journal of National University of Defense Technology

基　　金：国家重大科技专项资助项目(2017-Ⅳ-0009-0046)。

摘　　要：为了自动实现含气膜孔涡轮叶片寿命的可靠性设计优化,减少其有限元计算时间成本,提出了含气膜孔涡轮叶片的非结构局部网格参数化方法。该网格参数化方法将叶片划分为参数化区域和非参数化区域,分别设计非参数化区域的网格以及参数化区域的网格控制点,更新气膜孔的形状和位置后,保持非参数化区域的网格不变,重构参数化区域的网格。相比于结构网格的全局变形方法,该方法能够在保证有限元计算精度的同时,很大程度上缩减有限元的计算时间,有效提高可靠性设计优化的效率。In order to meet the RBDO(reliability-based design optimization)requirement for the life of turbine blade with film holes by automatic programmed control,the local parameterization method was proposed on the basis of the unstructured mesh,which significantly reduces the time costs of FEA(finite element analysis).The turbine blade was separated into two regions:the parameterized region and the non-parameterized region.After the meshes of the non-parameterized region and control points of the parameterized region were completed,only the meshes of parameterized region were required to be reconstructed when the geometry of film holes was updated.Compared with the global deformation method based on the structured mesh,the proposed method dramatically reduces the time costs of FEA while ensuring the accuracy of finite element calculation,which highly improves the efficiency of RBDO.

关 键 词：网格参数化 有限元分析 含气膜孔涡轮叶片 可靠性设计优化 

分 类 号：V228[航空宇航科学与技术—飞行器设计]