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

作　　者：王祥锋 王松涛 韩万金 

机构地区：[1]School of Energy Science and Engineering,Harbin Institute of Technology

出　　处：《Journal of Harbin Institute of Technology(New Series)》2010年第1期112-118,共7页哈尔滨工业大学学报（英文版）

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.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.

关 键 词：response surface models genetic algorithm transonic compressor optimization design numerical simulation 

分 类 号：O357.1[理学—流体力学] U463[理学—力学]