Numerical simulation of highly loaded multi-stage fan/compressor of a turbofan engine

According to high-altitude and low Reynolds number aerodynamic performance requirements of a turbofan engine, the fan/compressor on 0 km and 21 km operating conditions were simulated using three-dimensional (3-D) numerical simulation software Numeca. The results show that: the three-dimensional numerical simulation results of the 4-stage fan are in good agreement with the experimental results, and the precision can meet the engineering requirements; from 0 km to 21 km altitude, the inlet blade chord Reynolds number is reduced from 10⁶ to 10⁵, the mass flow rate is reduced by 2%~3%, the total pressure ratio is decreased a bit, and the efficiency is decreased by 3%; in the 3-D numerical simulation of 9-stage compressor, air bleeding is considered; from 0 km to 21 km altitude, the inlet blade chord Reynolds number is also reduced from 10⁶ to 10⁵, the mass flow rate and total pressure ratio are decreased a bit, and the attenuation of adiabatic efficiency increases from 4% to 7% with the decrease of speed.