Abstract: The method of centrifugal blade modeled by camber modeling method on basis of rule is studied. In meridional plane, the distribution of camber radius along axis is designed. In the plane, the distribution of camber azimuthal angle along axis is designed considering the flow parameters. The camber is created by combining the meridional curve and plane curve. The Bézier curve is employed to describe the curves and G2 continuous is obtained at the curve joints by upgrading. The centrifugal blade profile is generated by shifting thickness along the camber normal direction. The origin data for approximation model is sampled in design space by Latin hyper cube method as a method of design of experiment. Approximation model which represents the relationship between design parameters and responses is created by kriging model. The performance of compressor is improved on the basis of the approximation model, which reduces the design cycle.

Key words: Aircraft engines, Approximation model, Camber modeling, Centrifugal blade profile design, Compressors, Meridian line, z-θ plane curve