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 turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing.

Abstract: A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Abstract: A turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing.

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 turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area which includes at least two compressor disks (2.1-2.5) and a turbine area which includes at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement which includes at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.

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 fluid flow machine has a stator, a rotor which is supported so as to be rotatable relative to the stator, and a brush seal which seals a gap formed between the stator and rotor in a radial direction to prevent the passage of fluid. The brush seal has a brush holder and a plurality of sealing bristles, each of which has a first end that is fastened to the brush holder and a second end that contacts a sealing surface. The sealing surface is rotationally displaceable relative to the second ends of the respective sealing bristles. The sealing surface is formed by a circumferential surface of an intermediate sleeve which is arranged between the stator and rotor and which radially divides the gap.

Abstract: A turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area which includes at least two compressor disks (2.1-2.5) and a turbine area which includes at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement which includes at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.

Abstract: A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

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 pipeline duct through a discharge opening (17) of a vane support housing (1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ring (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support housing (1) in the horizontal direction due to their free spaces (11, 12, 13).