Purpose: the purpose of this work is to investi gate the total pressure losses in the input guide vane s in the rotor wheel and the guide vanes of the axial compressor stage ta king into account their gas-dynamic interference. Methods: the study was carried out by numerical simulation of three-dimensional flow in the stage of an axial compressor. An unstructured adaptive computational grid is constructed. The gas dynamic calculation of the flow in th e stage of the axial compressor is performed using the Navier-Stokes syst em of equations which was clos ed by the SST turbulent model. Results: a series of gas-dynamic flow calculations was performe d at different values of the axial velocity at the inlet to the compressor stage. The circuit velocity at the peripheral radius in the calculated mode was u= 238.64 m/s. The coefficient of velocity at the entrance to the stage varied in the range c λ =0.35...0.7. Based on the calculation results the dependences of the total pressure loss coefficients from th e input velocity coefficient for various elemen ts of the stage of the axial compressor were constructed. Analysis of the results of th e study shows that the great est contribution to the overa ll balance of total pressure losses is made by losses in the guide vanes. Discussion: losses in the guide vanes increa se due to the gas-dynamic interference of the rotor wheel a nd the guide vanes. The mutual influence of the blade rows of the rotor wheel and the guide vanes leads to a significant tr ansformation of the velocities and pressures in the interblade channels. As a consequence there is a redistribution of losses caused by circumferential and radial flow irregularity end-flow and centrifugal forces. It can be expected that a reduction in the level of losses in the step of the axial compressor can be achieved by influencing the boundary layer in the end clea rance of the rotor wheel.