Blade platform with damper restraint
AssigneeUnited Technologies Corporation
InventorsCharles Thistle, Mohamed Hassan
Life of this patent
Estimating the term…
Abstract
A gas turbine engine, having: a disk; a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk; a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades; and a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.
Claims20
A section of a gas turbine engine, comprising:
- a disk;
- a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk;
- a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades;
- and
- a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.
A gas turbine engine, comprising:
- a compressor section;
- a turbine section;
- a disk, wherein the disk is a portion of the compressor section or a portion of the turbine section;
- a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk;
- a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades;
- and
- a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.
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 the damper seal with at least two protrusions extending from an interior surface of a cavity defined by the adjoining platforms, wherein the at least two protrusions contact a peripheral edge portion of the damper seal when it is adjacent to the seam defined by the adjoining platforms of the blades.
Dependencies are inferred from the claim text.