Design optimization of transonic compressor stage using CFD and response surface model

作     者：王祥锋 王松涛 韩万金 

作者机构：School of Energy Science and EngineeringHarbin Institute of Technology 

出 版 物：《Journal of Harbin Institute of Technology(New Series)》 (哈尔滨工业大学学报（英文版）)

年 卷 期：2010年第17卷第1期

页      码：112-118页

摘      要：In order to shorten the design period, the paper describes a new optimization strategy for computationally expensive design optimization of turbomachinery, combined with design of experiment (DOE), response surface models (RSM), genetic algorithm (GA) and a 3-D Navier-Stokes solver(Numeca Fine). Data points for response evaluations were selected by improved distributed hypercube sampling (IHS) and the 3-D Navier-Stokes analysis was carried out at these sample points. The quadratic response surface model was used to approximate the relationships between the design variables and flow parameters. To maximize the adiabatic efficiency, the genetic algorithm was applied to the response surface model to perform global optimization to achieve the optimum design of NASA Stage 35. An optimum leading edge line was found, which produced a new 3-D rotor blade combined with sweep and lean, and a new stator one with skew. It is concluded that the proposed strategy can provide a reliable method for design optimization of turbomachinery blades at reasonable computing cost.

主 题 词：响应面模型 优化策略 跨音速压气机 设计阶段 CFD Stokes方程 响应曲面模型 叶轮机械 

学科分类：0810[工学-土木类] 080704[080704] 080103[080103] 08[工学] 082304[082304] 0807[工学-电子信息类] 080204[080204] 0805[工学-能源动力学] 0802[工学-机械学] 0812[工学-测绘类] 0801[工学-力学类] 0823[工学-农业工程类] 

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