The tip-leakage vortex of the rotor blade for a pump-jet propulsor not only reduces the cavitation performance of the propulsor, but also causes significant tip leakage pressure pulsation and unsteady excitation force, thereby reducing the acoustic performance of the propulsor. Therefore, pump-jet tip-leakage vortex control is an effective way to improve the acoustic performance of the propulsor. A tip-vortex control method based on the tip-winglet has been proposed for a pump-jet propulsor with pre-swirl stators. High-precision numerical simulation method is then used to compare and analyze the propulsion performance, flow field structure and pressure pulsation of the pump-jet propulsor before and after suppressing tip vortices. The results show that the rotor tip vortex control method based on the tip-winglet can significantly suppress the development of the pump-jet tip vortices and the pressure pulsation in tip clearance, however, it has little impact on the hydrodynamic performance of the propulsor. It can provide references for the acoustic optimization of the pump-jet propulsor.