Design Optimization of Turbomachinery Using Three-Dimensional Navier- Stokes Analysis

초록

Numerical optimization techniques for aerodynamic design of turbomachinery based on three-dimensional Navier-Stokes analysis are presented. Two different applications of the response surface optimization method to turbomachinery design are introduced; one is to optimize the shape of forward-curved blades centrifugal fan, and the other is one of previous works to optimize the shape of an axial-flow compressor rotor. Due to the large number of blades in forward-curved blades centrifugal fan, the flow inside of the fan is regarded as steady flow by introducing the impeller force models for economic calculations. Four design variables, i.e., location of cut off, radius of cut off, expansion angle of scroll and width of impeller, were selected to optimize the shapes of scroll and blades. In the design of compressor rotor, three design variables were selected to optimize the stacking line of the blade. Data points for response evaluations were selected by D-optimal design. As a main result of the optimizations, the efficiency was successfully improved in both cases. It was found that the optimization process provides reliable design of these kinds of turbomachinery with reasonable computing time.