Numerical simulation of aerodynamic performance of scaled fan of a civil high-bypass-ratio turbofan engine

According to the testing demand for the half-scaled fan of a civil high-bypass-ratio turbofan engine, the aerodynamic performance of scaled fan was simulated using three-dimensional CFD software. The effects of geometry scale, elastic recovery angle and bypass-ratio on the performance of the fan were also analyzed. The numerical simulation results show that the design objectives for the scaled fan can be met basically under all kinds of corrected rotating speed. When the geometry of the fan was scaled down to the half, the adiabatic efficiency of the bypass and core passages decrease by 1.26% and 0.77%, respectively. Under 80% corrected rotating speed, 0.36 degree reduction of the elastic recovery angle at fan tip could expand the stall margin by 4.04%, while the total pressure ratio and the adiabatic efficiency decreased at near design point. The total pressure ratio-mass flow characteristic and adiabatic efficiency-mass flow characteristic of the bypass and core passages for turbojet engine were represented a band of curves within a certain scope, under the bypass-ratio effect.