The method of replacing the blade row forces with distributed bulk body force source terms was developed to simulate fan flow field with inlet distortion.The fan with clean inlet and inlet steady total pressure distortion in an aeroengine were simulated respectively.It demonstrates that the results of fan with clean inlet agree well with the solutions of RANS(Reynolds-averaged Navier-Stokes).In the case with inlet distortion

this code can obtain the propagation of inlet distortion correctly.The unsteady simulation shows that large-scale strong reaction and three-dimentional transportation were main property of flow field with inlet distortion. The attraction of the distributed bulk body force model is obvious in that it can be relatively independent of the empiricism while at the same time demands much less computer resources.