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US 2012/0057988 A1Published application
Rotor for a turbomachine
AssigneeMTU Aero Engines AG
InventorFrank Stiehler
Life of this patent
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Abstract
The invention relates to a rotor (10) for a turbomachine, in particular for a gas turbine, having a basic rotor body (12) and a plurality of blades (14), wherein at least one damping element (24) is provided in the circumferential direction between adjacent blades (14) of the rotor (10).
Claims16
A rotor (10) for a turbomachine, in particular for a gas turbine,
- having a basic rotor body (12) and a plurality of blades (14),
- is hereby characterized in that
- at least one damping element (24) is provided in the circumferential direction between adjacent blades (14) of the rotor (10).
Dependencies are inferred from the claim text.