Damper for a turbine rotor assembly
A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with 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 greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate.
1. 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 greater than an area of the forward plate in the plane transverse to the longitudinal structure;
a pocket on the forward face of the forward plate, the pocket having an area greater than half the area of the forward plate, the width and height of the pocket being greater than half the width and height, respectively, of the forward plate, and a depth of the pocket being between about 25-50% of a thickness of the forward plate; and
the aft face of the forward plate including a recess that extends along the entire width of the forward plate, wherein the recess is positioned below the pocket.
2. The damper of claim 1 , wherein a cross-sectional area of the longitudinal structure in the plane transverse to the longitudinal structure is I-shaped, and the longitudinal structure includes a transverse notch at an intersection of the longitudinal structure with the aft face of the forward plate.
3. 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, and wherein the inverted V-shaped upper portion of the forward plate and the aft plate extends along a length to form tapered surfaces.
4. The damper of claim 1 , further including a nub projecting from a lower portion of the aft face of the aft plate.
5. The damper of claim 4 , further including a rectangular-shaped discourager extending in an aft direction from the aft face of the aft plate.
6. The damper of claim 5 , 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.
7. 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 having a width and a height, the forward plate including a forward face and an aft face, the forward plate further including,
a pocket on the forward face of the forward plate, the pocket having an area greater than half the area of the forward plate, the width and height of the pocket being greater than half the width and height, respectively, of the forward plate, and a depth of the pocket being between about 25-50% of a thickness of the forward plate, and
a recess on the aft face extending along the entire width of the forward plate, the recess being positioned below the pocket;
an aft plate having an area larger than the forward plate along the width and height dimension; and
a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.
8. The damper of claim 7 , wherein a depth of the recess is between about 20-50% of a thickness of the forward plate.
9. The damper of claim 7 , wherein a cross-sectional area of the longitudinal structure in the plane transverse to the length dimension is I-shaped, and 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.
10. The damper of claim 7 , wherein a lower portion of the forward plate includes a biasing lip that extends aft in the length dimension.
11. The damper of claim 10 , wherein the biasing lip is positioned below the recess and extends along the entire width of the forward plate.
12. The damper of claim 7 , wherein an upper portion of the forward plate and an upper portion of the aft plate includes an inverted V shape.
13. 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 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;
a pocket on the forward face of the forward plate, the pocket having an area greater than half the area of the forward plate, the width and height of the pocket being greater than half the width and height, respectively, of the forward plate, and a depth of the pocket being between about 25-50% of a thickness of the forward plate; and
a recess extending along the entire width of the forward plate positioned below the pocket on the aft face of the forward plate.
14. The damper of claim 13 , wherein a lower portion of the forward plate includes a biasing lip that extends along the entire width of the forward plate and projects aft from the forward plate.
15. The damper of claim 14 , wherein a depth of the recess is between about 20-50% of the thickness of the forward plate.