A blading design method for axial/centrifugal compressor airfoils using arbitrary camber lines

A blading design method for both axial and centrifugal compressor blades was discussed by using arbitrary camber lines.This method was based on through flow calculation.Three dimensional blades consistent with the result of through flow calculation can be obtained by modifying the distribution of velocity circulation.Meanwhile,it can control main blade/splitter blading and the shape of trailing edge of the airfoil.It has been applied to the design of compressor blades of some micro-engines,and fairly ideal airfoils are obtained.Also,this method can be used for optimization of compressor blades.