Pre-formed faceted turbine blade damper seal
AssigneeRaytheon Technologies Corporation
InventorsVladimir Skidelsky, Carlos Calixtro, Matthew B. DeGostin, John E. Paul, Mohamed Hassan, Charles Thistle, Jeffrey Michael Jacques
Life of this patent
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Abstract
A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.
Claims20
A damper seal for a turbine blade of a gas turbine engine, the damper seal comprising:
- an upper portion;
- a first downwardly curved portion;
- and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is pre-formed in a curve along the entire width as it extends along the length.
A turbine disk of a gas turbine engine having a plurality of turbine blades each of the plurality of turbine blades being secured to the turbine disk, at least one of the plurality of turbine blades comprising:
- a root;
- a platform located between the root and an airfoil of the at least one of the plurality of turbine blades, wherein platforms of adjacent turbine blades of the plurality of turbine blades of the disk define a cavity;
- and
- a damper seal received in the cavity the damper seal comprising:
- an upper portion;
- a first downwardly curved portion;
- and
- a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is pre-formed in a curve along the entire width as it extends along the length, the upper portion being positioned to cover a mate face gap between platforms of adjacent turbine blades of the disk.
A method of damping vibrations between adjoining blades of a gas turbine engine, comprising:
- locating a damper seal adjacent to a mate face gap defined by adjacent platforms of blades secured to a disk of the gas turbine engine, the damper seal comprising an upper portion;
- a first downwardly curved portion;
- and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is pre-formed in a curve along the entire width as it extends along the length.
Dependencies are inferred from the claim text.