Turbine blade damper seal

Patent metadata

Field	Value
Publication number	US-10113434-B2
Application number	US-201213362552-A
Country	US
Kind code	B2
Filing date	Jan 31, 2012
Priority date	Jan 31, 2012
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

First claim

What is claimed is:

1. A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf, the damper seal comprising:
a central body portion having a first end region, an opposing second end region, and a width;
a first portion extending from the first end region of the central body portion, wherein the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion, wherein the first portion includes a first another tab that extends substantially perpendicularly to the first outwardly extending tabs, and the first another tab extends away from the central body portion such that the first outwardly extending tabs are located between the central body portion and the first another tab; and
a second portion extending from the opposing second end region of the central body portion.

2. The damper seal as recited in claim 1 wherein the second portion includes second outwardly extending tabs that define a second enlarged portion that has a second width greater than the width of the central body portion.

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

4. The damper seal as recited in claim 2 wherein the second portion includes a second another tab that extends substantially perpendicularly to the second outwardly extending tabs, and the second another tab extends away from the central body portion such that the second outwardly extending tabs are located between the central body portion and the second another tab.

5. The damper seal as recited in claim 1 wherein a portion of the damper seal engages a groove in a turbine disk lug of a turbine disk.

6. The damper seal as recited in claim 1 wherein the central body includes a projection that defines an opening, and the opening receives a lug of a turbine blade to align the damper seal relative to the turbine blade.

7. The turbine blade as recited in claim 1 wherein the first portion has a first height and the second portion has a second height, and the second height is greater than the first height.

8. The turbine blade as recited in claim 1 wherein the central body portion is curved.

9. The turbine blade as recited in claim 1 wherein the damper seal is substantially c-shaped.

10. A turbine blade comprising:
a root received in a slot of a turbine disk;
a blade;
a platform located between the root and the blade, wherein the platform includes a retention shelf, and a cavity is defined between a lower surface of the platform and the retention shelf; and
a damper seal received in the cavity of the turbine blade, the damper seal including a central body portion having a first end region, an opposing second end region, a width, a first portion extending generally downward from the first end region of the central body portion, and a second portion extending generally downward from the opposing second end region of the central body portion, wherein the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion, wherein the first portion includes a first another tab that extends substantially perpendicularly to the first outwardly extending tabs, and the first another tab extends away from the central body portion such that the first outwardly extending tabs are located between the central body portion and the first another tab.

11. The turbine blade as recited in claim 10 wherein the second portion includes second outwardly extending tabs that define a second enlarged portion that has a second width greater than the width of the central body portion.

12. The turbine blade as recited in claim 10 wherein the damper seal is formed from stamped sheet metal.

13. The turbine blade as recited in claim 10 wherein the first enlarged portion rests on the retention shelf of the turbine blade.

14. The turbine blade as recited in claim 11 wherein the second portion includes a second another tab that extends substantially perpendicularly to the second outwardly extending tabs, and the second another tab extends away from the central body portion such that the second outwardly extending tabs are located between the central body portion and the second another tab.

15. The turbine blade as recited in claim 10 wherein a portion of the damper seal engages a groove in a turbine disk lug of the turbine disk.

16. The turbine blade as recited in claim 10 wherein the central body includes a projection that defines an opening, and the opening receives a lug on the lower surface of the platform of the turbine blade to align the damper seal relative to the turbine blade.

17. The damper seal as recited in claim 10 wherein the first portion has a first height and the second portion has a second height, and the second height is greater than the first height.

18. The damper seal as recited in claim 10 wherein the central body portion is curved.

19. The damper seal as recited in claim 10 wherein the damper seal is substantially c-shaped.

Assignees

• Snyder Daniel A
• Lana Kyle Charles
• Sandoval Jonathan Perry
• Virkler Scott Daniel
• Taraskevich Jaimie
• Otero Edwin
• United Technologies Corp

Inventors

• Snyder Daniel A
• Lana Kyle Charles
• Sandoval Jonathan Perry
• Virkler Scott Daniel
• Taraskevich Jaimie
• Otero Edwin

Classifications

• F01D5/3007

  of axial insertion type · CPC title

• F01D11/006

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

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/22 Primary

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title