Abstract: A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.

Abstract: A coupling element 2, 52 is disclosed for arrangement between shrouds 14,16 of adjacent rotor blades 4, 6, the coupling element having force-transmission surfaces 28, 30 for bounding damping gaps 12a, 12b between shrouds 14, 16, and a rotor having at least one coupling element 2, 52 of this type.

Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).

Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Abstract: A method for producing an integrally bladed rotor, in particular a gas turbine rotor, comprises the following steps:—Providing a blade (12) having a lower blade foot that has a joining surface (18);—Retaining the blade (12) in a retaining unit (20); and—Exciting the blade (12) to oscillate about an axis of rotation. A device for carrying out the method comprises a retaining unit, in which blade (12) can be solidly clamped in place, and an oscillating unit (24) that transmits translational oscillations to the retaining unit in a plane substantially parallel to joining surface (18), and a fixation unit (30) for establishing the axis of rotation.

Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Abstract: A method for producing an integrally bladed rotor, in particular a gas turbine rotor, by means of joining, comprises the following steps:—Providing a blade (10) having a joining surface;—Providing a retaining mechanism having two clamping jaws (28);—Retaining the blade (10) at two opposite points of blade (10) by means of clamping jaws (28) in a purely force-closed manner; and—Pressing the blade (10) retained in a force-closed manner onto a basic rotor body, so that blade (10) is aligned independently in a joining position. A device for producing an integrally bladed rotor comprises a retaining mechanism for a blade (10) having two clamping jaws (28), and by pressing these jaws together, blade (10) is retained at two opposite points in a purely force-closed manner; and a mechanism for pressing blade (10) retained in a force-closed manner onto a basic rotor body, in such a way that blade (10) is aligned independently in a joining position.

Abstract: A coupling element 2, 52 is disclosed for arrangement between shrouds 14,16 of adjacent rotor blades 4, 6, the coupling element having force-transmission surfaces 28, 30 for bounding damping gaps 12a, 12b between shrouds 14, 16, and a rotor having at least one coupling element 2, 52 of this type.

Abstract: A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.

Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).