An intuitive parameterization method with inherently high-order differentiability for compressor blade sections based on ellipse hierarchical deformation

作     者：Chuanrui SI Jinxin CHENG Zhengqing ZHU Zhitong CHEN Qinglong HAO Chuanrui SI;Jinxin CHENG;Zhengqing ZHU;Zhitong CHEN;Qinglong HAO

作者机构：School of Mechanical Engineering and AutomationBeihang UniversityBeijing 100191China School of Mechanical EngineeringUniversity of Science and Technology BeijingBeijing 100083China Zaozhuang Beihang Machine Tool Innovation Research Institute Co.LtdZaozhuang 277500China Ningbo Institute of TechnologyBeihang UniversityNingbo 315832China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2023年第36卷第8期

页      面：74-90页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the Fundamental Research(No.JCKY2021206B057)which is undertaken by Zaozhuang Beihang Machine Tool Innovation Research Institute Co. Ltd China 

主　　题：Aerodynamics Blade sections Compressors Deformation Ellipse Parameterization 

摘      要：Shape parameterization has a crucial influence on the optimal solution of aerodynamic *** paper proposes a novel parameterization method for compressor blade sections based on the three-level deformation of the ellipse,which simultaneously satisfies the requirements of flexibility,smoothness,intuitiveness,and *** proposed method,the first-level deformation directly controls nine key geometric parameters to construct the blade section profile,and then the second-and third-level deformations are performed respectively to coarsely and finely modify the profile while keeping the key geometric parameters *** three levels of deformation effectively decompose the design space without destroying the ellipse’s infinite differentiability,allowing designers to work only with intuitive shape-related parameters to design blade sections with inherently high-order *** verify the effectiveness,six existing blade sections are first fitted and then one of them is selected for a three-level *** results show that the geometry and aerodynamic performance of the fitted and the original blade sections are in good agreement,and the loss coefficient of the optimized blade section is reduced by a total of 36.41%,with 27.34%,8.45%,and 0.62%reductions for the first to the third level,***,the proposed parameterization method facilitates the design of lower-loss and higher-load compressor blade sections.