초록 ▼

The invention relates to a rotor for a turbo machine, having rotating blades (12), which are joined to a basic rotor body (14), whereby a damping element (24) for damping blade vibrations is provided between blade platforms (10) of at least two adjacent rotating blades (12), damping element (24) bei

The invention relates to a rotor for a turbo machine, having rotating blades (12), which are joined to a basic rotor body (14), whereby a damping element (24) for damping blade vibrations is provided between blade platforms (10) of at least two adjacent rotating blades (12), damping element (24) being arched radially upward along its axial extent relative to an axis of rotation of the rotor. In addition, the invention relates to a method for manufacturing, repairing, and/or overhauling a rotor for a turbo machine, in which rotating blades (12) are joined to a basic rotor body (14), whereby a damping element (24) for damping blade vibrations is disposed between at least two adjacent rotating blades (12). In this case, damping element (24) is arched radially upward along its axial extent relative to an axis of rotation of the rotor.

대표청구항 ▼

1. A rotor for a turbo machine having rotating blades (12), which are joined to a basic rotor body (14), in which a damping element (24) for damping blade vibrations is disposed at least partially in a gap defined between blade platforms (10) of at least two adjacent rotating blades (12), wherein th

1. A rotor for a turbo machine having rotating blades (12), which are joined to a basic rotor body (14), in which a damping element (24) for damping blade vibrations is disposed at least partially in a gap defined between blade platforms (10) of at least two adjacent rotating blades (12), wherein the damping element (24) is arched radially upward along its axial extent relative to an axis of rotation of the rotor and wherein a sealing element (26), by means of which an exchange of flow medium in the radial direction between adjacent rotating blades (12) can be at least reduced thereby, is disposed between at least two adjacent rotating blades (12) with the sealing element (26) being disposed radially above damping element (24). 2. The rotor according to claim 1, wherein the sealing element (26) is disposed radially above damping element (24), sealing element (26) is joined with damping element (24) and/or is arched radially upward along its axial extent relative to an axis of rotation of the rotor. 3. The rotor according to claim 1, wherein the damping element (24) includes a central region; the central region of the damping element (24) is formed weaker with respect to bending and torsion than the ends of damping element (24) and/or that the damping element is formed with multiple parts and/or is designed mirror-symmetrical in cross section. 4. The rotor according to claim 1, wherein at least one cavity (22) is formed underneath a blade platform (10) of at least one rotating blade (12), the damping element (24) and/or optionally the sealing element (26) being disposed in regions within this cavity. 5. The rotor according to claim 1, wherein the blade platform (10) of at least one rotating blade (12) comprises a guide element (28), by means of which a side and/or a bottom of damping element (24) can be supported. 6. The rotor according to claim 5, further characterized in that guide element (28) is disposed in the region of the high-pressure (HD) side and/or the low-pressure (ND) side of the rotor. 7. The rotor according to claim 1, wherein an inner-lying contact surface (30) is provided in the radially outer region of at least one blade platform (10), and damping element (24) and/or optionally a sealing element (26) can be brought into contact with this contact surface, at least during the operation of the rotor. 8. The rotor according to claim 1, wherein the blade platform (10) of at least one rotating blade (12) forms a blade shroud (19) for at least a partial boundary of a flow channel of the turbo machine. 9. The rotor according to claim 1, wherein the rotating blades (12) are joined to the basic rotor body (14) in a detachable manner or cohesively. 10. The rotor according to claim 1, wherein the rotor is configured for use in a turbo machine. 11. The rotor according to claim 1, wherein the damping element (24) includes a central region; the central region of the damping element (24) is formed weaker with respect to bending and torsion than the ends of damping element (24). 12. The rotor according to claim 1, wherein the damping element (24) has a cross-sectional surface in the form of an isosceles trapezoid in its radially upper end region, the isosceles trapezoid having a first side extending along a first upper surface, the isosceles trapezoid having a second side extending along a second upper surface, the first and second upper surfaces being configured to contact respective contact surfaces on the adjacent blades. 13. The rotor according to claim 1, wherein the damping element is shaped in an arch that has a peak between a first end and a second end, the peak being further radially upward than the first end and the second end. 14. A method for manufacturing, repairing, and/or overhauling a rotor for a turbo machine, comprising the steps of: joining rotating blades (12) to a basic rotor body (14);disposing a damping element (24) for damping blade vibrations between at least two adjacent rotating blades (12); wherein the damping element (24) is arched radially upward along its axial extent relative to an axis of rotation of the rotor andmoving the damping element (24) from a low-pressure (ND) side and/or a high-pressure (HD) side of a rotor at least partially in a gap defined between blade platforms (10). 15. The method according to claim 14, further comprising the step of: moving the damping element (24) along inner-lying contact surfaces (30) of adjacent blade platforms (10), the contact surfaces (30) being arched radially upward along their axial extent relative to an axis of rotation of the rotor. 16. The method according to claim 14, further comprising the step of: disposing a sealing element (26), by means of which an exchange of flow medium in the radial direction between adjacent rotating blades during the operation of the turbo machine can be at least reduced thereby, between at least two adjacent rotating blades (12). 17. The method according to claim 14, wherein the damping element (24) has a cross-sectional surface in the form of an isosceles trapezoid in its radially upper end region, the isosceles trapezoid having a first side extending along a first upper surface, the isosceles trapezoid having a second side extending along a second upper surface, the first and second upper surfaces being configured to contact respective contact surfaces on the adjacent blades.