A method was developed for the design of non-axial turbomachine airfoils with arbitrary surfaces.The method can be applied to the design of centrifugal compressor and mixed flow compressor blades and vaned diffusers.Especially

the employed blade surface setting method is that letting the blade thickness be distributed as a triple spline function.Also the application of splitter blade to centrifugal compressor and mixed flow compressor and rotor splitter-blades design were introduced in this paper.Fairly ideal airfoils were obtained.This method of airfoil design has been validated to be operational and applicable by CFD simulation.It built a sound foundation for further aerodynamic optimization of those non-axial flow type turbomachines.