The effects of turbomachinery blade bow and sweep on aerodyna mic loading distribution of the blade are investigated.A general definition of sweep angle is given in the case of turbomachinery.By means of linearized small perturbation theory

the effects of each factor are analyzed respectively

then a numerical simulation for three-dimensional viscous flow is used to verify and elaborate the analytical results.It is shown that the blade bow

twist and leading edge sweep are effective in adjusting the loading distribution on the blade surface.It is possible to make rational and effective use of the three dimensional blading to adjust the loading distributions both spanwise and chordwise

it thus provides a set of means for blading optimization.