Disk supported damper for a gas turbine engine

1. A rotor disk assembly for a gas turbine engine, comprising:

a rotor disk that defines an axis;

a damper pivot support that extends radially outward from a rim of the rotor disk, the damper pivot support comprising an aperture that defines a pivot axis parallel to the axis; and

a damper assembly pivotably attached to the damper pivot support by a pin through the aperture, the damper assembly pivotable about the pivot axis.

2. The assembly as recited in claim 1 , wherein the damper pivot support extends from each of a multiple of lugs of the disk.

3. The assembly as recited in claim 1 , wherein the damper pivot support extends from every other of a multiple of lugs of the disk.

4. The assembly as recited in claim 1 , further comprising a first damper and a second damper pivotably attached to the damper pivot support by the pin through the aperture, the first damper and the second damper independently pivotable about the pivot axis.

5. The assembly as recited in claim 4 , wherein the first damper comprises a first contact surface and the second damper comprises a second contact surface.

6. The assembly as recited in claim 5 , wherein the first contact surface is shaped to contact a suction side of a first blade and the second contact surface is shaped to contact a pressure side of a second blade.

7. The assembly as recited in claim 6 , wherein the first contact surface and the second contact surface are angled toward the rim.

8. The assembly as recited in claim 6 , wherein the first contact surface is shaped to contact the suction side of the first blade below a platform of the first blade and the second contact surface is shaped to contact the pressure side of the second blade below a platform of the second blade.

9. The assembly as recited in claim 6 , wherein the first contact surface is shaped to contact the suction side of the first blade but not a platform of the first blade and the second contact surface is shaped to contact the pressure side of the second blade but not a platform of the second blade.

10. The assembly as recited in claim 5 , further comprising a first counterweight that extends from the first contact surface opposite the pivot axis and a second counterweight that extends from the second contact surface opposite the pivot axis.

11. The assembly as recited in claim 10 , wherein the first contact surface and the second contact surface are angled away from the rim.

12. The assembly as recited in claim 5 , wherein the first contact surface and the second contact surface are opposite a respective hinge section.

13. The assembly as recited in claim 12 , wherein the respective hinge sections form apertures which fit around the pin such that the first contact surface and the second contact surface are arms which extend therefrom.

14. The assembly as recited in claim 1 , wherein the aperture is circular.

15. The assembly as recited in claim 14 , further comprising a first damper and a second damper pivotably attached to the damper pivot support by a pin through the aperture.

16. A rotor disk assembly for a gas turbine engine, comprising:

a rotor disk that defines an axis;

a first rotor blade mounted within a first blade slot in a rim of the rotor disk;

a second rotor blade mounted within a second blade slot in the rim of the rotor disk;

a damper pivot support that extends radially outward from a rim of a lug in the rotor disk, the lug between the first blade slot and the second blade slot, the damper pivot support comprising an aperture that defines a pivot axis parallel to the axis;

a first damper independently pivotable about a pin along the pivot axis to contact the first blade in response to centrifugal force; and

a second damper independently pivotable about the pin along the pivot axis to contact the second blade in response to centrifugal force.

17. The assembly as recited in claim 16 , wherein the first damper comprises a first contact surface and the second damper comprise a second contact surface, the first contact surface is shaped to contact a suction side of a first blade and the second contact surface is shaped to contact a pressure side of a second blade.

18. The assembly as recited in claim 17 , wherein the first contact surface is shaped to contact the suction side of the first blade below a platform of the first blade and the second contact surface is shaped to contact the pressure side of the second blade below a platform of the second blade.

19. The assembly as recited in claim 18 , wherein the first contact surface and the second contact surface are angled toward the rim.

20. The assembly as recited in claim 18 , further comprising a first counterweight that extends from the first contact surface opposite the pivot axis and a second counterweight that extends from the second contact surface opposite the pivot axis.

21. The assembly as recited in claim 20 , wherein the first contact surface and the second contact surface are angled away from the rim.

22. The assembly as recited in claim 18 , wherein the first contact surface and the second contact surface are opposite a respective hinge section, the respective hinge sections form apertures which fit around the pin such that the first contact surface and the second contact surface are arms which extend therefrom.

23. A method to dampen a rotor blade of a gas turbine engine, comprising:

pivotably mounting a damper assembly to a damper pivot that extends radially outward from a rim of a lug in a rotor disk, the lug between a first blade slot and a second blade slot of the rotor disk, a damper pivot support defines a pivot axis along a pin parallel to an axis defined by the rotor disk; and

independently pivoting a first damper and a second damper of the damper assembly about the pivot axis of the pin to respectively contact a first blade and a second blade in response to centrifugal force, a first contact surface of the first damper and a second contact surface of the second damper contacting the respective blades below a platform of the respective first blade and second blade.

24. The method as recited in claim 23 , wherein the first contact surface and the second contact surface are angled toward the rim and pivot away from the rim in response to the centrifugal force.

25. The method as recited in claim 23 , wherein the first contact surface and the second contact surface are angled away from the rim and pivot toward the rim in response to the centrifugal force.