Internally damped blade
View Patent ↗A blade includes an airfoil portion which defines at least one cavity with a damper located within the cavity, the damper includes a corrugated surface.
1. A blade comprising:
an airfoil portion which defines at least one internal cavity, said internal cavity at least partially bounded by a chordwise rib; and
a damper located within said internal cavity, said damper includes a corrugated surface transverse to a span of the airfoil portion, said corrugated surface configured to provide a chordwise mode damping and a bending mode damping.
2. The blade as recited in claim 1 , wherein said airfoil portion extends from a platform portion of a fan blade.
3. The blade as recited in claim 1 , wherein said internal cavity is at least partially bounded by a spanwise rib.
4. The blade as recited in claim 1 , wherein said damper is oriented such that a peak-to-peak thickness of said corrugated surface is defined along a thickness of said airfoil portion between a concave pressure side and a convex suction side of said airfoil portion.
5. The blade as recited in claim 1 , wherein said corrugated surface is oriented generally transverse to a leading edge and a trailing edge of the airfoil portion.
6. The blade as recited in claim 1 , wherein said damper includes a curved end section which abuts said chordwise rib.
7. The blade as recited in claim 1 , wherein said damper defines a material thickness in the range of 0.015 to 0.030 inches (0.4-0.8 mm).
8. The blade as recited in claim 1 , further comprising anon-metallic coating on said damper.
9. The blade as recited in claim 1 , wherein said damper includes a curved end section each of which abuts a chordwise rib.
10. The blade as recited in claim 1 , wherein said damper is not integral with said airfoil portion.
11. The blade as recited in claim 1 , wherein said damper is movable within said internal cavity.
12. The blade as recited in claim 1 , wherein said damper is loosely fit within said internal cavity such that when no centrifugal force exists, no contact forces exist between said damper and an inner surface of said internal cavity.
13. The blade as recited in claim 1 , wherein said damper is oriented such that a centrifugal force along said span of said airfoil portion causes said damper to load up against said chordwise rib so as to develop a normal contact force between at least one corrugation of said corrugated surface and an inner surface of said internal cavity.
14. A blade comprising:
an airfoil portion which defines at least one internal cavity, said internal cavity at least partially bounded by a chordwise rib; and
a damper located within said internal cavity, said damper includes a corrugated surface transverse to a span of the airfoil portion, said damper configured to provide a multi-mode damping.
15. The blade as recited in claim 14 , wherein said multi-mode damping includes chordwise mode damping.
16. The blade as recited in claim 14 , wherein said multi-mode damping includes bending mode damping.
17. The blade as recited in claim 14 , wherein said corrugated surface is oriented generally transverse to a leading edge and a trailing edge of the airfoil portion.
18. The blade as recited in claim 14 , wherein said multi-mode damping orients said damper such that a centrifugal force along said span of said airfoil portion causes said damper to load up against said chordwise rib so as to develop a normal contact force between at least one corrugation of said corrugated surface and an inner surface of said internal cavity.
19. A blade comprising:
an airfoil portion which defines at least one internal cavity, said internal least partially bounded by a chordwise rib; and
a damper located within said internal cavity, said damper includes a corrugated surface transverse to a span of the airfoil portion, said damper deforms in response to a centrifugal force to fit said internal cavity.
20. The blade as recited in claim 19 , wherein said fit is a friction fit under the centrifugal force.
21. The blade as recited in claim 19 , wherein said fit is an interference fit under the centrifugal force.
22. The blade as recited in claim 19 , wherein said damper is oriented such that a peak-to-peak thickness of said corrugated surface is defined along a thickness of said airfoil portion between a concave pressure side and a convex suction side of said airfoil portion to provide said fit.
23. The blade as recited in claim 22 , wherein said corrugated surface is oriented generally transverse to a leading edge and a trailing edge of the airfoil portion.
24. The blade as recited in claim 19 , wherein said damper deforms in response to said centrifugal force to fit said internal cavity such that said centrifugal force along said span of said airfoil portion causes said damper to load up against said chordwise rib so as to develop a normal contact force between at least one corrugation of said corrugated surface and an inner surface of said internal cavity.