Pre-formed faceted turbine blade damper seal

Patent metadata

Field	Value
Publication number	US-11377967-B2
Application number	US-201916705451-A
Country	US
Kind code	B2
Filing date	Dec 6, 2019
Priority date	Dec 6, 2019
Publication date	Jul 5, 2022
Grant date	Jul 5, 2022

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.

First claim

What is claimed is:

1. 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.

2. The damper seal as in claim 1 , wherein the width of the upper portion has a constant radius profile running along the entire width as it extends along the length.

3. The damper seal as in claim 1 , wherein the first downwardly curved portion includes a first tab and a second tab each extending in opposing directions with respect to the first downwardly curved portion, and a third tab that extends from the first tab and the second tab of the first downwardly curved portion in the same general direction as the first downwardly curved portion; and the second downwardly curved portion includes a first tab and a second tab each extending in opposing directions with respect to the second downwardly curved portion, and a third tab that extends from the first tab and the second tab of the second downwardly curved portion in the same general direction as the second downwardly curved portion.

4. The damper seal as in claim 1 , wherein a height of the second downwardly curved portion relative to the upper portion is longer than a height of the first downwardly curved portion relative to the upper portion.

5. The damper seal as in claim 1 , wherein the damper seal is formed from stamped sheet metal.

6. The damper seal as in claim 3 , further comprising a mistake proofing tab extending from the third tab of the first downwardly curved portion and a mistake proofing opening located in the third tab of the second downwardly curved portion.

7. The damper seal as in claim 3 , wherein the width of the upper portion has a constant radius profile running along the entire width as it extends along the length.

8. The damper seal as in claim 7 , wherein a height of the second downwardly curved portion relative to the upper portion is longer than a height of the first downwardly curved portion relative to the upper portion.

9. The damper seal as in claim 8 , wherein the damper seal is formed from stamped sheet metal.

10. 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.

11. The turbine disk as in claim 10 , wherein the width of the upper portion has a constant radius profile running along the entire width as it extends along the length.

12. The turbine disk as in claim 10 , wherein the first downwardly curved portion includes a first tab and a second tab each extending in opposing directions with respect to the first downwardly curved portion, and a third tab that extends from the first tab and the second tab of the first downwardly curved portion in the same general direction as the first downwardly curved portion; and the second downwardly curved portion includes a first tab and a second tab each extending in opposing directions with respect to the second downwardly curved portion, and a third tab that extends from the first tab and the second tab of the second downwardly curved portion in the same general direction as the second downwardly curved portion.

13. The turbine disk as in claim 10 , wherein a height of the second downwardly curved portion relative to the upper portion is longer than a height of the first downwardly curved portion relative to the upper portion.

14. The turbine disk as in claim 10 , wherein the damper seal is formed from stamped sheet metal.

15. The turbine disk as in claim 12 , wherein the damper seal further comprises a mistake proofing tab extending from the third tab of the first downwardly curved portion and a mistake proofing opening located in the third tab of the second downwardly curved portion.

16. The turbine disk as in claim 12 , wherein the width of the upper portion has a constant radius profile running along the entire width as it extends along the length.

17. The turbine disk as in claim 16 , wherein a height of the second downwardly curved portion relative to the upper portion is longer than a height of the first downwardly curved portion relative to the upper portion.

18. The turbine disk as in claim 10 , wherein the turbine disk is a first stage of a high pressure turbine.

19. 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.

20. The method as in claim 19 , wherein the width of the upper portion has a constant radius profile running along the entire width as it extends along the length.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Skidelsky Vladimir
• Calixtro Carlos
• Degostin Matthew B
• Paul John E
• Hassan Mohamed
• Thistle Charles
• Jacques Jeffrey Michael

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F05D2230/60

  Assembly methods · CPC title