Blade Parameterization and Aerodynamic Design Optimization for a 3D Transonic Compressor Rotor

作     者：Naixing Chen Hongwu Zhang Yanji Xu Weiguang Huang Institute of Engineering Thermophysics,Chinese Academy of Sciences,P.O.Box 2706,Beijing 100080,CHINA.E-mail:nxc@*** Fax:+8610-62573335 

作者机构：Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing China 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2007年第16卷第2期

页      码：105-114页

摘      要：The present paper describes an optimization methodology for aerodynamic design of turbomachinery combined with a rapid 3D blade and grid generator （RAPID3DGRID）, a N.S. solver, a blade parameterization method （BPM）, a gradient-based parameterization-analyzing method （GPAM）, a response surface method （RSM） with zooming algorithm and a simple gradient method. By the use of blade parameterization method a transonic com- pressor rotor can be expressed by a set of polynomials, and then it enables us to transform coordinate-expressed blade data to parameter-expressed and then to reduce the number of parameters. With changing any one of the parameters and by applying grid generator and N.S. solver, we can obtain several groups of samples. Here only ten parameters were considered to search an optimized compressor rotor. As a result of optimization, the adiabatic efficiency was increased by 1.73%.

主 题 词：Aerodynamic optimization blade optimization compressor bladings 

学科分类：080103[080103] 08[工学] 080104[080104] 0805[工学-能源动力学] 0702[理学-物理学类] 0801[工学-力学类] 

核心收录：

D　O　I：10.1007/s11630-007-0105-3

馆 藏 号：203137804...