Abstract: A compressor for a turbomachine, with at least one rotor disc and a space that is at least partially enclosed by the at least one rotor disc and that is arranged axially in front of or behind the at least one rotor disc, wherein vortex reducers are arranged inside the space, wherein the vortex reducers are connected to the structural components in a form-fitted and/or in a frictionally engaged manner partially via first scallops at a first structural component and partially via second scallops at a second structural component that is adjacent to the first structural component in the axial direction, wherein the first scallops and/or second scallops are arranged at a retaining ring, which can be connected or is connected to the first rotor disc and/or the second rotor disc. What is further described is a method for mounting a compressor.

Abstract: A rotor arrangement, with a rotor for an engine having a rotor disc that extends along a circumferential direction about a central axis, and at least one balancing element that is attached at the rotor disc for balancing the rotor. At least one attachment section projecting axially with respect to the central axis is embodied at the rotor disc, and the at least one balancing element engages around the axially projecting attachment section.

Abstract: A compressor for a turbomachine, with at least one rotor disc and a space that is at least partially enclosed by the at least one rotor disc and that is arranged axially in front of or behind the at least one rotor disc, wherein vortex reducers are arranged inside the space, wherein the vortex reducers are connected to the structural components in a form-fitted and/or in a frictionally engaged manner partially via first scallops at a first structural component and partially via second scallops at a second structural component that is adjacent to the first structural component in the axial direction, wherein the first scallops and/or second scallops are arranged at a retaining ring, which can be connected or is connected to the first rotor disc and/or the second rotor disc. What is further described is a method for mounting a compressor.

Abstract: A tube-type vortex reducer for the conduction of cooling air in a compressor (1) of a gas turbine, having radial secondary air tubes (2) arranged in a disk interspace (5) and attached to a compressor disk (3) at their radially outward end sections (33). Radially inward sections (30) of the secondary air tubes (2) are located fittingly and radially outward in recesses (31) of locating pads (32) of a compressor disk (3), and the radially outward sections (33) of the secondary air tubes (2) are carried radially shiftable in recesses (34) of locating arms (35) of the compressor disk (3) and are secured against radially inward movement by locking elements (36).

Abstract: A tube-type vortex reducer for the conduction of cooling air in a compressor (1) of a gas turbine, having radial secondary air tubes (2) arranged in a disk interspace (5) and attached to a compressor disk (3) at their radially outward end sections (33). Radially inward sections (30) of the secondary air tubes (2) are located fittingly and radially outward in recesses (31) of locating pads (32) of a compressor disk (3), and the radially outward sections (33) of the secondary air tubes (2) are carried radially shiftable in recesses (34) of locating arms (35) of the compressor disk (3) and are secured against radially inward movement by locking elements (36).