Today a crucial objective of the aerospace industry is to realize lighter blades with a lower environmental impact. To pursue these objectives, it is necessary to find out innovative types of blades characterized by a new geometry feature and a lighter material. This thesis work is developed in collaboration with Avio Aero and its goal is to analyze aeroelastic issues of LPT blade, in particular the aim of this work is to show the impact of the different Boundary Conditions at the interlocking on the flutter stability. The entity of the contact at the interlocking must be studied, it is not possible to establish it in a deterministic way because during the blade’s service life causing flutter instability it could change.