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US 2013/0280083 A1Published application
Rotor blade arrangement for a turbo machine
AssigneeMTU Aero Engines AG
InventorAndreas Hartung
Life of this patent
Estimating the term…
Abstract
In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.
Claims13
1-9. (canceled)
A moving blade system for a turbomachine, comprising:
- at least one moving blade;
- and
- at least one tuning mass movably situated in at least one cavity of the moving blade system, at least one of the tuning mass and the cavity being adapted so that the tuning mass rests against an inner wall of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.
Dependencies are inferred from the claim text.