Design optimization of transonic compressor stage using CFD and response surface model
WANG Xiang-feng, Wang Song Tao, Han Wan Jin
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Abstract:
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.
Key words: response surface models genetic algorithm transonic compressor optimization design numerical simulation
DOI:10.11916/j.issn.1005-9113.2010.01.021
Clc Number:TH45
Fund:
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Design optimization of transonic compressor stage using CFD and response surface model
本站小编 哈尔滨工业大学/2019-10-23
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