This project focuses on the reduction of forced response in multi-stage aircraft engine compressors. The interaction between rotors and stators from the different stages generates unsteady pressure fields which excite the vibration modes in the blades and can lead to failure due to high cycle fatigue. Thus, reduction techniques, such as non-uniform vane spacing, are studied, which could decrease the amplitude of the excitations or shift them into frequencies that do not resonate with the blades. Tyler-Sofrin mode analysis helps understand the aeroacoustic effects that are generated by the multi-stage interactions, which can propagate or decay depending if the mode frequency is above or below cut-on, and are very important to forced response in compressors.