By integrating genetic algorithm with response surface methodology

this paper developed an optimization system

with introduction of a quasi-three-dimensional through-flow design code and a blade formatting code.While a three-dimensional CFD (computational fluid dynamics) solver was involved

this paper established a numerical aerodynamic optimization platform for three-dimensional blades of axial-flow compressors.The optimization in this paper mainly has four features.First

it applies the conventional inverse design method instead of common CAGD (computer aided geometric design) parameterization method to generate a three-dimensional blade.Second

it chooses aerodynamic parameters with physical meaning as optimization design variables instead of purely geometrical parameters.Third

it presents a stage-by-stage optimization strategy about the multistage turbomachinery optimization.Fourth

it introduces the visual analysis method into optimization.The above techniques were applied

first

to a two-stage axial-flow fan for its maximum mass flow rate

and then

to the reformed two-stage axial-flow fan for its maximum adiabatic efficiency.The work distributions were taken as design variables

which were parametrically represented by means of Bézier curves.The two examples elucidate that not only the techniques mentioned above are appropriate and effective in engineering

but also the design guidance for similar inverse design problems can be obtained from the optimization results.