| 摘要 |
According to the invention, in a rotor blade arrangement for a turbo machine, in particular a gas turbine, having at least one rotor blade (1), wherein the rotor blade arrangement has at least one cavity (3) in which at least one tuning mass (2) is arranged in a movable manner, the tuning mass and/or the cavity are/is adapted such that the tuning mass bears against an inner wall (3.1) of the cavity in a predefined first operating state of the turbo machine, and moves away from the inner wall at least intermittently in a second predefined operating state of the turbo machine. |
