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A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal s

A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate.

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1. A damper for a turbine rotor assembly of a gas turbine engine, comprising: a width dimension, a height dimension, and a length dimension;a forward plate;an aft plate including a larger area than the forward plate along the width and height dimensions,a width-wise centrally positioned nub that pro

1. A damper for a turbine rotor assembly of a gas turbine engine, comprising: a width dimension, a height dimension, and a length dimension;a forward plate;an aft plate including a larger area than the forward plate along the width and height dimensions,a width-wise centrally positioned nub that projects aft in the length dimension from a lower portion of the aft plate;a rectangular-shaped discourager located above the nub and extending aft in the length dimension; anda longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate. 2. The damper of claim 1, wherein a cross-sectional area of the longitudinal structure in the plane transverse to the length dimension is I-shaped. 3. The damper of claim 1, wherein the forward plate includes a pocket in the form of a recess in the length dimension. 4. The damper of claim 1, wherein the longitudinal structure includes an inverted U-shaped notch extending in the width dimension at an intersection of the longitudinal structure with the forward plate. 5. The damper of claim 1, wherein a lower portion of the forward plate includes a biasing lip that extends aft in the length dimension. 6. The damper of claim 5, wherein the biasing lip extends along the entire width dimension of the forward plate. 7. The damper of claim 1, wherein an upper portion of the forward plate and an upper portion of the aft plate includes an inverted V shape. 8. A damper for a turbine rotor assembly of a gas turbine engine, comprising: a forward plate including a forward face and an aft face;an aft plate including a forward face and an aft face, the aft face of the forward plate being connected to the forward face of the aft plate with a longitudinal structure, an area of the aft plate in a plane transverse to the longitudinal structure being larger than an area of the forward plate in the plane transverse to the longitudinal structure, and wherein a cross-sectional area of the longitudinal structure in the plane transverse to the longitudinal structure is I-shaped; anda nub projecting from a lower portion of the aft face of the aft plate. 9. The damper of claim 8, wherein the forward face of the forward plate includes a pocket. 10. The damper of claim 8, wherein the longitudinal structure includes a transverse notch at an intersection of the longitudinal structure with the aft face of the forward plate. 11. The damper of claim 10, wherein the aft face of the forward plate includes a recess that extends along an entire width of the forward plate. 12. The damper of claim 8, wherein an upper portion of the forward plate and an upper portion of the aft plate includes an inverted V shape. 13. The damper of claim 12, wherein the inverted V-shaped upper portion of the forward plate and the aft plate extends along a length to form tapered surfaces. 14. The damper of claim 8, wherein the nub is width-wise centrally positioned on the aft face of the aft plate. 15. The damper of claim 8, further including a rectangular-shaped discourager extending in an aft direction from the aft face of the aft plate. 16. The damper of claim 15, wherein the discourager is located above the nub and extends from one side of the aft plate to an opposite side of the aft plate. 17. A damper for a turbine rotor assembly of a gas turbine engine, comprising: a forward plate;an aft plate connected to the forward plate with a longitudinal structure, an area of the aft plate in a plane transverse to the longitudinal structure being larger than an area of the forward plate in the plane transverse to the longitudinal structure,an inverted U-shaped notch extending transverse to the longitudinal structure at an intersection of the longitudinal structure with the forward plate; anda width-wise centrally positioned nub projecting aft from a lower portion of the aft plate. 18. The damper of claim 17, wherein a lower portion of the forward plate includes a biasing lip that extends along an entire width of the forward plate and projects aft from the forward plate. 19. The damper of claim 17, wherein an upper portion of the forward plate and an upper portion of the aft plate includes an inverted V shape.