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 

机构地区：[1]School of Mechanical Engineering and Automation,Beihang University,Beijing 100191,China [2]School of Mechanical Engineering,University of Science and Technology Beijing,Beijing 100083,China [3]Zaozhuang Beihang Machine Tool Innovation Research Institute Co.,Ltd,Zaozhuang 277500,China [4]Ningbo Institute of Technology,Beihang University,Ningbo 315832,China

出　　处：《Chinese Journal of Aeronautics》2023年第8期74-90,共17页中国航空学报（英文版）

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

摘　　要：Shape parameterization has a crucial influence on the optimal solution of aerodynamic optimization.This 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 compactness.In 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 unchanged.These 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 continuity.To verify the effectiveness,six existing blade sections are first fitted and then one of them is selected for a three-level optimization.The 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,respectively.Therefore,the proposed parameterization method facilitates the design of lower-loss and higher-load compressor blade sections.

关 键 词：Aerodynamics Blade sections Compressors DEFORMATION ELLIPSE PARAMETERIZATION 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]