Abstract: A gas turbine with a compressor having stator side guide blades and rotor side moving blades, a burner a combustion chamber; with a turbine); with a diffuser arranged downstream of the compressor, which has an inside wall and an outside wall and; an intermediate housing following the outside wall. An outlet side guide blade ring of stator side, outlet side guide blades (30a) of the compressor has an inner shroud and an outer shroud. First fastening devices are formed on the outer shroud (34) of the guide blade ring via which the guide blade ring is attached to the intermediate housing, second fastening devices are formed, on the inner shroud (33) of the guide blade ring via which the inside wall of the diffuser is directly attached to the guide blade ring.

Abstract: A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

Abstract: A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

Abstract: The rotor (5) of a gas turbine containing a compressor part (1) and a turbine part (3) is mounted in an axial thrust bearing (19) and in two radial journal bearings (16, 17). One of the bearings is a journal bearing (16) arranged in the intake area of the compressor part (1) and the other journal bearing (17) together with the thrust bearing (19) is arranged in the area of the turbine part (3).

Abstract: The rotor (5) of a gas turbine containing a compressor part (1) and a turbine part (3) is mounted in an axial thrust bearing (19) and in two radial journal bearings (16, 17). One of the bearings is a journal bearing (16) arranged in the intake area of the compressor part (1) and the other journal bearing (17) together with the thrust bearing (19) is arranged in the area of the turbine part (3).

Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).