A blade for a gas turbine engine. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper seal received in the cavity, the damper seal having a main body portion that extends along a major axis of the damper seal between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion each extend towards the root when the damper seal is located in the cavity and wherein the damper seal has a variable thickness along at least a portion of a minor axis of the damper seal that extends between opposite peripheral edges of the main body portion.