Turbine blade for a gas turbine engine

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

a turbine rotor having a plurality of turbine blade slots extending radially inward from an outer rim, each turbine blade slot extending radially from an inner end to the outer rim and extending axially from a forward end to an aft end of the rotor, and a groove positioned in the aft end of the rotor;

a plurality of turbine blades having an airfoil and a root structure extending from opposite sides of a platform, the root structure of each turbine blade including a portion shaped to be received in a corresponding turbine blade slot of the rotor; and

a damper positioned between the root structures of two adjacent turbine blades of the plurality of turbine blades, the damper extending axially from the forward end to the aft end of the rotor and including a forward plate at the forward end and an aft plate at the aft end, wherein a front face of the forward plate forms a flush surface with front surfaces of the root structures of the two adjacent turbine blades, and wherein a nub extends in an aft direction from a lower portion of a lower extension of the aft plate and is positioned in the groove of the turbine rotor.

2. The turbine rotor assembly of claim 1 , wherein the groove is positioned between two adjacent turbine blade slots.

3. The turbine rotor assembly of claim 1 , wherein an aft face of the nub is positioned facing a surface of the rotor within the groove.

4. The turbine rotor assembly of claim 1 , wherein the nub is width-wise centrally positioned on the lower extension.

5. The turbine rotor assembly of claim 1 , wherein the platforms of the two adjacent turbine blades form an overhanging ledge above the flush surface.

6. The turbine rotor assembly of claim 5 , further including a seal plate attached to the forward end of the rotor, the seal plate extending upwards from a first end below the blade slots to a second end located proximate the outer rim of the rotor.

7. The turbine rotor assembly of claim 6 , wherein the second end of the seal plate includes a circumferential lip that extends from the seal plate to form an overhanging ledge below the flush surface.

8. The turbine rotor assembly of claim 1 , wherein the aft plate of the damper extends outwards from the aft end of the rotor.

9. A turbine rotor assembly of a gas turbine engine, comprising:

a turbine rotor extending from a forward end to an aft end, the turbine rotor including a plurality of turbine blade slots extending radially inwards from an outer rim, and a groove positioned at the aft end;

a plurality of turbine blades having a root structure extending below a platform, a portion of the root structure of each turbine blade being positioned in a corresponding turbine blade slot of the rotor; and

a damper positioned between the root structures of two adjacent turbine blades of the plurality of turbine blades, the damper including,

a forward plate at the forward end of the rotor and an aft plate at the aft end of the rotor, and

a nub that extends in an aft direction from a lower portion of the aft plate, wherein the nub is positioned in the groove of the turbine rotor.

10. The turbine rotor assembly of claim 9 , wherein the nub is width-wise centrally positioned on the aft plate.

11. The turbine rotor assembly of claim 9 , wherein a front face of the forward plate of the damper forms a flush surface with front surfaces of the root structures of the two adjacent turbine blades.

12. The turbine rotor assembly of claim 11 , wherein the platforms of the two adjacent turbine blades form an overhanging ledge above the flush surface.

13. The turbine rotor assembly of claim 9 , further including a seal plate attached to the forward end of the rotor, the seal plate extending upwards from a first end below the blade slots to a second end located proximate the outer rim of the rotor.