Blade for a rotor assembly of a turbine engine

A blade adapted for mounting on a rotor disc for a gas turbine engine, the blade comprising:

• a blade root;
• an airfoil;
• platform segments between the airfoil and the blade root and extending laterally from the blade, the platform segments having a curved profile defining a platform recess on a root side of the platform segments, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket;
• and
• the blade root having a rear surface, a recessed region at least partially defined in the rear surface, the recessed region having a surface forming a face seal, the recessed region being adapted to abut a corresponding surface on a projection of the rotor disc, the recessed region being recessed into the rear surface of the blade root by a depth, the depth adapted to correspond to an axial dimension of the projection of the rotor disc, such that the recessed region is adapted to house the projection of the rotor disc, whereby the rear end surface of the blade root is adapted to be flush with a rearmost surface of the projection.