Three-Dimensional Aerodynamic Characteristics of Fan Rotor with Large Bypass Ratio in Distorted Flow Field

A three-dimensional numerical calculation code based on body force model has been developed and used to predict the intake fan of high bypass ratio turbofan engine performance with inlet distortion. The program can predict the characteristic curve of the fan rotor with high accuracy, and can describe the flow field of the fan reliably. The program is used to study the fan rotor characteristics of turbofan engine with large bypass ratio in circumferential distortion flow field, and the three-dimensional characteristics of the distorted flow field are obtained. The results show that the nununiformity of total pressure be weakened, total pressure distortion always decays through the fan. The total pressure distortion in the inlet will induce the total temperature distortion in the rotor blade trailing edge. Distortion transfer coefficients in the different height of rotor blade are different, and they distribute along the radial direction.