Blade platform with damper restraint
AssigneeRaytheon Technologies Corporation
InventorsCharles Thistle, Mohamed Hassan
Life of this patent
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Abstract
A blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein 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 adjacent to a portion of the lateral edge of the damper seal.
Claims14
A blade for a gas turbine engine, comprising:
- a root;
- a platform located between the root and an airfoil, wherein the platform defines a cavity;
- a damper seal supported by a first radially inner surface of the platform;
- a groove in the first radially inner surface, the groove having a groove bottom radially outward of the first radially inner surface, wherein the groove is positioned such that a lateral edge of the damper seal enters the groove as the damper seal moves circumferentially toward the root.
A disc of a gas turbine engine having a plurality of blades, each of the plurality of blades comprising:
- a root;
- a platform located between the root and an airfoil, wherein the platforms of adjacent blades of the plurality of blades are located adjacent to each other in order to define a cavity;
- and
- a single damper restraint located on a suction side of the blade, wherein only the single damper restraint retains any lateral edge of a damper seal when the damper seal is received in the cavity and spans across a seam between adjacent platforms such that portions of the damper seal extend past the seam and along an underside of the adjacent platforms, the lateral edge of the damper seal extending 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 is covering the seam and wherein the damper restraint extends along and is adjacent to a portion of the lateral edge of the damper seal when the damper seal is covering the seam.
A method of damping vibrations between adjacent blades of a gas turbine engine, comprising:
- sealing a seam defined by adjacent platforms of a pair of blades of a disc of the gas turbine engine by locating a damper seal over the seam wherein portions of the damper seal extend past the seam and along underside surfaces of the adjacent platforms when the damper seal is located over the seam;
- and
- restraining movement of the damper seal in a direction away from the seam by retaining only a single lateral edge of the damper seal with a damper restraint formed in the underside surface of one of the adjacent platforms of the pair of blades, wherein the one of the adjacent platforms of the pair of blades extends from a suction side of one of the pair of blades.
Dependencies are inferred from the claim text.