A modified design of a fan was described

on the basis of enough performance and flow field analysis of original fan

in order to satisfy the more thrust requirement of a turbo-fan engine. The modified design method was: the design tool was “a general blading design system and its application for axial/centrifugal compressor”. According to the similitude theory

at the precondition of the equivalence of converse mass flow and converse revolution speed at the second stage inlet

the increase of the mass flow was growing with the pressure ratio. By CFD computation and analysis

all the performances met the requirement and the design result was perfect. The results show that as the speed of the fan increases 1.1 percent

the mass flow increases 7.1 percent

the pressure ratio increases 7.4 percent

the efficiency increases 2.9 percent

and the stall marge increases 0.8 percent. Analysis and valuation of the performance and matching characteristic indicate that this design can satisfy the more thrust requirement of the turbo-fan engine.