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US 6,607,359 B2Granted
Apparatus for passive damping of flexural blade vibration in turbo-machinery
AssigneeHood Technology Corporation
InventorAndreas H. von Flotow
Life of this patent
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Abstract
A rotor blade for a turbine engine rotor assembly is provided comprising a root, an airfoil, a platform, and a means for damping vibrations in the airfoil. The airfoil includes a pocket formed into a chordwise surface. The damper is received into the pocket, forming a surface flush with the airfoil. Relative movement between the damper and the airfoil cause vibrational movement to be damped and dissipated in the form of frictional energy.
Claims3
A rotor blade for a turbine engine rotor assembly, comprising:
- a) an airfoil, having a curvature and a pocket formed in a chordwise surface, said pocket open to said surface;
- and
- b) means for damping vibrations in said blade, said means including a damper,
- wherein said damper is received within said pocket and said damper is contoured to match the curvature of said airfoil,
- wherein one or more edges of said pocket are undercut as a means of locating and restricting motion of said damper in said pocket,
- wherein said damper is contoured to be received by said pocket with sufficient contact surface area, and
- wherein said damper is retained in said pocket using frictional forces acting on said contact surface area.
4 more elements
A method for damping vibrations in a rotor blade, comprising steps of:
- a) determining vibratory characteristics of said rotor blade, including determining where strain energy regions exist for selected modes of vibration within said airfoil;
- b) determining a geometry for one or more pockets in a chordwise surface of said airfoil, such that said pockets are located in high strain energy regions of said rotor blade;
- c) forming said pocket in said chordwise surface;
- and
- d) inserting a damper in said pocket.
2 more elements
Dependencies are inferred from the claim text.