Throughflow inverse design of a transonic fan stage based on CFD method

Abstract

In this paper, a throughflow method based on Computational Fluid Dynamics (CFD), which has emerged as a focal point in the field of turbomachinery design, is developed to be universally applied across the entire speed range. For the inverse problem, the distribution of circulation is specified along streamlines. To simulate the viscous dissipation effects, isentropic efficiency is manually input into the program. The results of a subsonic ideal rotor demonstrate the correctness of the inviscid module. To showcase the design capability to design transonic axial-flow turbomachinery, a fan stage featuring a total pressure ratio of 1.59 and a tip relative Mach number of 1.35 is designed. The results indicate that the performance parameters exhibit an error of less than 0.1%, effectively providing information regarding the airflow angle along the spanwise direction of blade rows.