Abstract: Described is a rotor disk (40) for a compressor (29, 32) of a gas turbine, in particular an aircraft gas turbine (10), the rotor disk having a main body (42), at least one rotor arm (44) projecting from the main body (42) in the axial direction (AR), the rotor arm (44) having, in a sectional view taken in a sectional plane defined by the axial direction (AR) and the radial direction (RR) a beginning portion (44a) merging into the main body (42); an end (44e) portion remote from the main body (42) and forming a kind of free end in the axial direction (AR), the beginning portion (44a) and the end portion (44e) being interconnected by an intermediate portion (44z), characterized in that the intermediate portion (44z) is curved with at least one radius of curvature (Ri, Ra).

Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Abstract: A rotor stage (200) for a turbomachine, including a plurality of rotor blades (9), a rotor main body (7) having at least two rotor arms (3) and a balancing assembly (1) for balancing the rotor stage (200). The rotor arm (3) configured downstream from the rotor main body (7) features the balancing assembly (1). The balancing assembly (1) is configured between the axial end region of the rotor arm (3) and the rotor disk (27) of the rotor main body (7). Furthermore, a rotor drum (17, 18) for a turbomachine and a rotor (1000) for a turbomachine.

Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Abstract: A rotor stage (200) for a turbomachine, including a plurality of rotor blades (9), a rotor main body (7) having at least two rotor arms (3) and a balancing assembly (1) for balancing the rotor stage (200). The rotor arm (3) configured downstream from the rotor main body (7) features the balancing assembly (1). The balancing assembly (1) is configured between the axial end region of the rotor arm (3) and the rotor disk (27) of the rotor main body (7). Furthermore, a rotor drum (17, 18) for a turbomachine and a rotor (1000) for a turbomachine.