TURBINE BLADE DAMPER SEAL

• US 20130195665A1
• Filed: 01/31/2012
• Published: 08/01/2013
• Est. Priority Date: 01/31/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Snyder, Daniel A., Sandoval, Jonathan Perry, Otero, Edwin, Lana, Kyle Charles, Virkler, Scott Daniel, Taraskevich, Jaimie
• Granted Patent: US 10,113,434 B2
• Time in Patent Office: Days
• US Class Current: 416/174
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

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 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.

2. The damper seal as recited in claim 1 wherein a second end region of 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 1 wherein the first enlarged portion rests on a retention shelf of a turbine blade.

5. The damper seal as recited in claim 1 wherein the first portion includes another tab that extends substantially perpendicularly to the first outwardly extending tabs.

6. The damper seal as recited in claim 2 wherein the second portion includes another tab that extends substantially perpendicularly to the second outwardly extending tabs.

7. 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.

8. 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.

9. 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 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.

10. The turbine blade as recited in claim 9 wherein a second end region of 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.

11. The turbine blade as recited in claim 9 wherein the damper seal is formed from stamped sheet metal.

12. The turbine blade as recited in claim 9 wherein the first enlarged portion rests on the retention shelf of the turbine blade.

13. The turbine blade as recited in claim 9 wherein the first portion includes another tab that extends substantially perpendicularly to the first outwardly extending tabs.

14. The turbine blade as recited in claim 10 wherein the second portion includes another tab that extends substantially perpendicularly to the second outwardly extending tabs.

15. The turbine blade as recited in claim 9 wherein a portion of a damper seal engages a groove in a turbine disk lug of the turbine disk.

16. The turbine blade as recited in claim 9 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. A turbine comprising:

a turbine disk including a plurality of lugs and a plurality of slots, wherein each of the plurality of lugs is located between two of the plurality of slots, and each of the plurality of lugs includes a tab that extends upwardly, wherein the tab has first section having an upper surface and a second section having an upper surface, the upper section of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour; and

a turbine blade, wherein the turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour,

wherein, when the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

18. The turbine as recited in claim 17, wherein an upper surface of each of the plurality of lugs includes an axial groove and a circumferential groove that intersects the axial groove, and the circumferential groove defines a rear surface of the tab.

19. The turbine as recited in claim 18, wherein the circumferential groove is deeper than the axial groove.

20. The turbine as recited in claim 18, wherein the axial groove receives a damper seal located under the platform.

21. The turbine as recited in claim 20, wherein a portion of the damper seal rests against the rear surface of the tab.

22. The turbine as recited in claim 17, wherein the upper surface of the first section of the tab is substantially parallel to the lower surface of the platform.