Unsteady numerical simulation of a 1.5-stage transonic axial compressor was carried out by using the fluid-structure iterative interaction method. The influence of the rotor-stator interaction on the high frequency dynamic load and aeroelastic response of rotor blade was studied. The generation mechanism of dynamic load

time domain and frequency domain characteristics

and blade aeroelastic response law were analyzed. The results show that aerodynamic force and aerodynamic torque fluctuations on rotor blade surface are mainly affected by the wake of upstream guide vane

and are weakly affected by the potential flow of downstream stator blade. The aerodynamic force fluctuation amplitude is the largest near 30% blade height

while the aerodynamic torque fluctuation amplitude is the largest near blade tip. In the spectrum of aerodynamic force and aerodynamic torque near the tip of rotor blade

the first three harmonics dominate. Dynamic load results in high frequency forced vibration of rotor blade

and the vibration signal spectrum of blade tip leading edge mainly includes the first three orders passing frequency of guide vane wake.