The effect of icing on turbo-machinery has been of recent interest due to certification requirements of engine operation and focus on optimum ice protection systems. In this project, we examine a STAGE 67A stator blade to represent a part of a turbo-machinery compressor stage. Numerical simulations use the Reynolds-Average Navier-Stokes (RANS) solver for the air flow coupled with Continuous Random Walk (CRW) for the droplet trajectory and impingement released upstream of stator blade. These results were coupled with LEWICE for ice formation on the stator blade. The overall methodology allows prediction of the impingement efficiency, the amount of ice formation, and the adverse effects on the aerodynamic performances. Changes in the flow field due to ice accretion can lead to boundary layer separations, which causes reduction in the flow turning angle and mass flow rate as well as increase in the total pressure loss. Icing accretion is significantly sensitive to droplet size, integration time, and temperature. However weak sensitivity was found with respect to turbulence and angle of attack.