Abstract
A three-dimensional (3D) blade design method for an axial
compressor transonic stage to optimize the aerodynamic
performance is presented in this paper. The blade is defined by
three profiles and a radial stacking line. Each profile is a multi
circular arc (MCA), and the stacking line is defined as a B-spline
curve with six design parameters. To ensure the off-design
performance, a multi-objective genetic algorithm (MOGA) is
applied. The objective functions are the efficiency, shock position
and leading edge pressure difference at the design point. Because
shock position and leading edge pressure difference can evaluate
the potential for stalling, the method can generate blades with a
wide operating range with just one performance prediction. This
method is applied in a transonic blade design. The result shows that
the efficiency of the optimized blade at the design point is increased
and the operation range is expanded compared with the original
blade.
