Static aeroelasticity analysis of a rotor blade using a Gauss-Seidel fluid-structure interaction method

作     者：Jiaxing Li Jiaqi Luo Yaolong Liu Zhonghua Han 

作者机构：School of Aeronautics and AstronauticsZhejiang UniversityHangzhou 310027China School of AeronauticsNorthwestern Polytechnical UniversityXi’an 710072China 

出 版 物：《Advances in Aerodynamics》 (空气动力学进展（英文）)

年 卷 期：2023年第5卷第1期

页      面：478-496页

核心收录：

学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0801[工学-力学（可授工学、理学学位）] 

基　　金：the Zhejiang Provincial Natural Science Foundation of China(Grant no.LXR22E060001) the National Science and Technology Major Project of China(Grant no.2017-II-0006-0020) the National Natural Science Foundation of China(Grant no.92152202) 

主　　题：Fluid-structure interaction Rotor blade Static aeroelasticity Data transfer aerodynamic performance 

摘      要：The present study introduces a Gauss-Seidel fluid-structure interaction(FSI)method including the flow solver,structural statics solver and a fast data transfer technique,for the research of structural deformation and flow field variation of rotor blades under the combined influence of steady aerodynamic and centrifugal *** FSI method is illustrated and validated by the static aeroelasticity analysis of a transonic compressor rotor blade,NASA Rotor *** improved local interpolation with data reduction(LIWDR)algorithm is introduced for fast data transfer on the fluid-solid interface of *** results of FSI calculation of NASA Rotor 37 show that when compared with the radial basis function(RBF)based interpolation algorithm,LIWDR meets the interpolation accuracy requirements,while the calculation cost can be greatly *** data transmission time is only about 1%of that of ***,the iteration step of steady flow computation within one single FSI has little impact on the converged aerodynamic and structural *** aerodynamic load-caused deformation accounts for nearly 50%of the *** effects of blade deformation on the variations of aerodynamic performance are given,demonstrating that when static aeroelasticity is taken into account,the choke mass flow rate increases and the peak adiabatic efficiency slightly *** impact mechanisms on performance variations are presented in detail.