| 摘要 |
A multi-stage rotor assembly for a gas turbine engine including a damper system that facilitates damping vibrations induced to the rotor assembly is described. 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.
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