In the last years, the aeronautical industry has had a continuous growth and expansion and the aircraft manufacturers have focused their efforts on improving efficiency and performance of existing engines. Most of these improvements come from recently developed analyses techniques applied to the main engine’s components. One of them is the Low-Pressure Turbine (LPT) which has a fundamental part on the overall efficiency of an aircraft engine. The design process of an LPT involves several disciplines such as Aeromechanics, Rotordynamics, Aeroelasticity. For these reasons, this thesis, carried out in collaboration with GE Avio Aero, is focused on the study of forced response analyses and wear behavior of a tip shrouded blade of a Low-Pressure Turbine.