Damper stacks for turbomachine rotor blades

Patent metadata

Field	Value
Publication number	US-11248475-B2
Application number	US-201916709050-A
Country	US
Kind code	B2
Filing date	Dec 10, 2019
Priority date	Dec 10, 2019
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

First claim

What is claimed is:

1. A rotor blade for a turbomachine, the rotor blade comprising:
a main body comprising a shank and an airfoil extending radially outwardly from the shank;
a platform surrounding the main body, the platform comprising a slash face; and
a damper stack disposed at the slash face and extending generally along an axial direction, the damper stack comprising a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin, wherein each of the plurality of damper pins extends between a first end and a second end, and wherein the first end of a first damper pin of the plurality of damper pins defines a spherical convex shape and the second end of a second damper pin of the plurality of damper pins defines a spherical concave shape, the second end of the second damper pin mating with the first end of the first damper pin.

2. The rotor blade of claim 1 , wherein each of the plurality of damper pins extends between the first end having the spherical convex shape and the second end having the spherical concave shape.

3. The rotor blade of claim 1 , wherein the first end of the first damper pin has an outward spherical shape, and the second end of the second damper pin has an inward spherical shape.

4. The rotor blade of claim 1 , wherein a length of each of the plurality of damper pins is defined between the first end and the second end of the damper pin, wherein the length of one of the damper pins of the plurality of damper pins is different from the length of another of the damper pins of the plurality of damper pins.

5. The rotor blade of claim 1 , wherein the damper stack further comprises a wire extending through each of the plurality of damper pins.

6. The rotor blade of claim 1 , wherein a groove is defined in the slash face, and wherein the damper stack is partially disposed in the groove.

7. The rotor blade of claim 1 , wherein the plurality of damper pins comprises a first end pin and a second end pin, the first end pin spaced apart from the second end pin along the axial direction, the first end pin and the second end pin each comprising a shoulder defined by a cutout portion.

8. The rotor blade of claim 7 , wherein each of the shoulders comprises a flat support surface.

9. The rotor blade of claim 8 , wherein a groove is defined in the slash face, wherein the damper stack is partially disposed in the groove, and wherein each of the shoulders is disposed in a shoulder slot portion of the groove.

10. A turbomachine, comprising:
a compressor section;
a combustor section;
a turbine section;
a plurality of rotor blades provided in at least one of the compressor section or the turbine section, each of the plurality of rotor blades comprising:
a main body comprising a shank and an airfoil extending radially outwardly from the shank;
a platform surrounding the main body, the platform comprising a slash face; and
a damper stack disposed at the slash face and extending generally along an axial direction, the damper stack comprising a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin, wherein each of the plurality of damper pins extends between a first end and a second end, and wherein the first end of a first damper pin of the plurality of damper pins defines a spherical convex shape and the second end of a second damper pin of the plurality of damper pins defines a spherical concave shape, the second end of the second damper pin mating with the first end of the first damper pin.

11. The turbomachine of claim 10 , wherein each of the plurality of damper pins extends between the first end having the spherical convex shape and the second end having the spherical concave shape.

12. The turbomachine of claim 10 , wherein the first end of the first damper pin has an outward spherical shape, and the second end of the second damper pin has an inward spherical shape.

13. The turbomachine of claim 10 , wherein a length of each of the plurality of damper pins is defined between the first end and the second end of the damper pin, wherein the length of one of the damper pins of the plurality of damper pins is different from the length of another of the damper pins of the plurality of damper pins.

14. The turbomachine of claim 10 , wherein the damper stack further comprises a wire extending through each of the plurality of damper pins.

15. The turbomachine of claim 10 , wherein a groove is defined in the slash face, and wherein the damper stack is partially disposed in the groove.

16. The turbomachine of claim 10 , wherein the plurality of damper pins comprises a first end pin and a second end pin, the first end pin spaced apart from the second end pin along the axial direction, the first end pin and the second end pin each comprising a shoulder defined by a cutout portion.

17. The turbomachine of claim 16 , wherein each of the shoulders comprises a flat support surface.

18. The turbomachine of claim 17 , wherein a groove is defined in the slash face, wherein the damper stack is partially disposed in the groove, and wherein each of the shoulders is disposed in a shoulder slot portion of the groove.

19. The turbomachine of claim 10 , wherein the plurality of rotor blades is provided in the turbine section.

20. The turbomachine of claim 10 , wherein the turbomachine is a gas turbine.

Assignees

• Gen Electric

Inventors

• Wondrasek Michael Anthony
• Potter Brian Denver
• Brittingham Robert Alan

Classifications

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D5/22 Primary

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

• F05D2250/241

  spherical · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title