Methods and apparatus for damping rotor assembly vibrations
AssigneeGeneral Electric Company
InventorDavid William Crall
Life of this patent
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Abstract
A multi-stage rotor assembly for a gas turbine engine includes a damper system that facilitates damping vibrations induced to the rotor assembly. The rotor assembly includes a blisk rotor including a plurality of rotor blades and a radially outer rim. The rotor blades are integrally formed with the rim and extend radially outward from the rim. The damper system is attached to rotor blades within at least one stage of the rotor assembly, and includes at least one layer of damping material and a cover sheet. The cover sheet is attached to the rotor blade with adhesive.
Claims19
A method of fabricating a rotor assembly for a gas turbine engine to facilitate damping vibrations induced to the rotor assembly, the rotor assembly including a radially outer rim and a plurality of rotor blades that extend radially outward from the radially outer rim, each of the rotor blades including an airfoil including a pair of opposing sidewalls, said method comprising the steps of:
- forming a cavity in each rotor blade airfoil that extends radially inward from the airfoil first sidewall towards the airfoil second sidewall;
- embedding a first layer of damping material within the airfoil cavity adjacent the airfoil;
- and
- attaching a constraining layer to the airfoil with adhesive, such that the constraining layer is adjacent the first layer of damping material;
- and
- attaching a cover sheet to the airfoil with adhesive, such that the cover sheet extends around a periphery of the airfoil cavity in sealing contact with the airfoil.
A rotor assembly for a gas turbine engine, said rotor assembly comprising a rotor comprising a radially outer rim and a plurality of rotor blades extending radially outward from said radially outer rim, each said rotor blade comprising an airfoil and a damper system comprising at least one layer of damping material and a cover sheet, said cover sheet attached to said rotor blade airfoil with adhesive, each said rotor blade airfoil further comprising a first sidewall and a second sidewall, and a cavity therebetween, said cavity extending partially from a said first sidewall towards said second sidewall, said damping system cover sheet having an outer perimeter larger than an outer perimeter of said sidewall cavity.
A gas turbine engine comprising a rotor assembly comprising a rotor comprising a radially outer rim and a plurality of rotor blades extending radially outward from said radially outer rim, each said rotor blade comprising an airfoil and a damper system comprising at least one layer of damping material and a cover sheet, said cover sheet attached to said rotor blade airfoil with adhesive such that said damping material is positioned between said airfoil and said damper system cover sheet, said damper system configured to damp vibrations induced to said rotor blades, each said rotor blade airfoil further comprising a first sidewall and a second sidewall, and a cavity therebetween, said cavity extending partially from a said first sidewall towards said second sidewall, said damping system cover sheet having an outer perimeter larger than an outer perimeter of said sidewall cavity.
Dependencies are inferred from the claim text.