Blade platform with damper restraint

A gas turbine engine, comprising:

• a disk;
• a plurality of blades secured to the disk, each of the blades having a root, and a platform located between the root and the blade, wherein a seam is defined by adjoining platforms of each of the blades when they are secured to the disk, wherein the platform of each of the plurality of blades defines a cavity and has a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein the damper seal covers the seam and the lateral edge of the damper seal extends between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and wherein the damper restraint extends along and contacts a portion of the lateral edge of the damper seal.

A method of damping vibrations between adjoining blades of a gas turbine engine, comprising:

• locating a damper seal adjacent to a seam defined by adjoining platforms of blades of the gas turbine engine;
• and
• restraining the movement of the damper seal in a direction away from the seam by retaining a lateral edge of the damper seal with a damper restraint formed in an underside surface of one of the adjoining platforms.