Cooled rotor blade with vibration damping device
A rotor blade for a rotor assembly is provided that includes a root, an airfoil, a platform, and a damper. The airfoil has at least one cavity. The platform is disposed between the root and the airfoil. The platform includes an inner surface, an outer surface, and a damper aperture disposed in the inner surface. The damper has a body and a base. The base and the damper aperture have mating geometries that enable the base to rotate within the damper aperture without substantial impediment from the mating geometries.
1. A rotor blade for a rotor assembly, comprising:
a root;
an airfoil having at least one cavity;
a platform disposed between the root and the airfoil, the platform having an inner surface, an outer surface, and a damper aperture disposed in the inner surface; and
a damper having a body and a base;
wherein the base and the damper aperture have mating geometries that enable the base to move within the aperture without substantial impediment from the mating geometries.
2. The rotor blade of claim 1 , wherein the mating geometries are such that the base is operable to rotate within the aperture without substantial impediment from the mating geometries.
3. The rotor blade of claim 1 , wherein the mating geometries are such that the base is operable to move axially within the aperture without substantial impediment from the mating geometries.
4. The rotor blade of claim 1 , wherein the mating geometries are such that the base is operable to move circumferentially within the aperture without substantial impediment from the mating geometries.
5. The rotor blade of claim 1 , wherein the mating geometries permit three degree of freedom movement between the base and the damper aperture during operation of the rotor blade.
6. The rotor blade of claim 5 , wherein a bearing portion of the base is spherically shaped.
7. The rotor blade of claim 5 , wherein a bearing portion of the base is conically shaped.
8. The rotor blade of claim 5 , wherein the damper aperture is toroidally shaped.
9. The rotor blade of claim 1 , wherein the damper further comprises a tang extending outwardly from the base.
10. The rotor blade of claim 9 , wherein the tang is operably shaped to retain engagement of the tang with the rotor blade.
11. The rotor blade of claim 9 , wherein the tang has a first cross-sectional profile and a second cross-sectional profile, and the first cross-sectional profile and the second cross-sectional profile are disposed substantially perpendicular to one another.
12. The rotor blade of claim 11 , wherein the first cross-sectional profile and the second cross-sectional profile are dissimilar in size.
13. The rotor blade of claim 11 , wherein the first cross-sectional profile and the second cross-sectional profile are oriented so as to be skewed from the airflow direction passing the tang during operation.
14. A rotor assembly, comprising:
a disk; and
a plurality of rotor blades selectively attachable to the disk, each rotor blade having a root, an airfoil having at least one cavity, a platform disposed between the root and the airfoil, wherein the platform has an inner surface, an outer surface, and a damper aperture disposed in the inner surface, and each rotor blade has a damper having a body and a base, wherein the base and the damper aperture have mating geometries that enable the base to rotate within the aperture without substantial impediment from the mating geometries.
15. The rotor assembly of claim 14 , wherein the mating geometries permit three degree of freedom movement between the base and the damper aperture during operation of the rotor blade.
16. The rotor assembly of claim 14 , wherein each damper further comprises a tang extending outwardly from the base.
17. The rotor assembly of claim 16 , further comprising a retainer ring disposed proximate the tang of each damper.
18. The rotor blade of claim 16 , wherein the tang is operably shaped to retain engagement of the tang with the rotor blade.
19. The rotor assembly of claim 16 , wherein each tang has a first cross-sectional profile and a second cross-sectional profile, and the first cross-sectional profile and the second cross-sectional profile are disposed substantially perpendicular to one another.
20. The rotor assembly of claim 16 , wherein the first cross-sectional profile and the second cross-sectional profile of each rotor blade are dissimilar in size.
21. The rotor assembly of claim 20 , wherein the first cross-sectional profile and the second cross-sectional profile are oriented so as to be skewed from the airflow direction passing the tang during operation.
22. A damper for use in a rotor blade having an airfoil, the damper comprising:
a base having a bearing surface portion shaped to permit movement of the damper within the rotor blade; and
a body extending outwardly from the base and receivable within said airfoil.
23. The damper of claim 22 , wherein the bearing surface portion is at least in part shaped spherically.
24. The damper of claim 22 , wherein the bearing surface portion is at least in part shaped conically.
25. The damper of claim 24 , wherein the tang is operably shaped to retain engagement of the tang with a rotor blade.
26. The damper of claim 22 , further comprising a tang extending outwardly from the base.
27. The damper of claim 26 , wherein the tang has a first cross-sectional profile and a second cross-sectional profile, and the first cross-sectional profile and the second cross-sectional profile are disposed substantially perpendicular to one another.
28. The damper of claim 27 , wherein the first cross-sectional profile and the second cross-sectional profile are dissimilar in size.