초록 ▼

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.

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.

대표청구항 ▼

1. 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 wi

1. 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. 2. A rotor blade according to claim 1, wherein centripetal forces acting on said damper tend to retain said damper within said pocket. 3. 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.