This paper addresses the gust response on the stator of a rotor/stator axial compressor, by decomposing the response into vortical and potential contributions. Experiments were conducted in a large-scale, low-speed compressor rig, with two axial gap cases — 10% and 30% chord — and at two time-mean loadings. To determine the gust response due to potential contribution, a two-step approach was taken. First, a panel code was used to determine the gust in the mid-gap plane for the rotor/stator configuration. Then, this calculated gust served as an inlet boundary of a Reynolds-averaged Navier-Stokes code for the stator cascade configuration. The vortical contributed gust response was found by subtracting the potential contributed response from the measured response. Results show that the vortical contributed response is largest near the instant when the rotor wake impinges at the stator leading edge. The potential contributed response reaches a maximum when the rotor trailing edge is axially upstream of the stator leading edge. The vortical contributed response dominates for all cases studied.