Abstract: A rotor of a gas turbine having two adjacent rotor discs, on each of which moving blades are fastened, an annular rotor component being arranged between the rotor discs and having at its opposite ends circumferential annular grooves, in each of which a circumferential fastening projection on the respective rotor disc engages. When the rotor is stationary a first outer flank of the first annular groove rests under pressure against a first outer flank of the first fastening projection and there is play between a first inner flank of the first annular groove and a first inner flank of the first fastening projection.

Abstract: Martensitic steel with Z phase, powder, and blank or component—alloy, at least including (in % by weight): carbon (C): 0.16%-0.24%, silicon (Si): 0.0%-0.08%, manganese (Mn): 0.04%-0.16% chromium (Cr): 10.6%-11.5%, molybdenum (Mo): 0.5%-0.9%, tungsten (W): 2.2%-2.6%, cobalt (Co): 3.0%-3.6%, nickel (Ni): 0.09%-0.19%, boron (B): 0.0035%-0.01%, nitrogen (N): 0.001%-0.025%, titanium (Ti): 0.01%-0.04%, copper (Cu): 1.20%-2.30%, optionally vanadium (V): 0.10%-0.30%, niobium (Nb): 0.02%-0.08%, aluminium (Al): 0.003%-0.06%, balance: iron (Fe).

Abstract: An alloy which includes at least the following (in % by weight): carbon (C): 0.15%-0.25%; silicon (Si): 0.0%-0.08%; manganese (Mn): 0.03%-0.20%; chromium (Cr): 9.5%-10.5%; molybdenum (Mo): 0.4%-1.0%; tungsten (W): 1.6%-2.4%; cobalt (Co): 2.5%-3.5%; nickel (Ni): 0.0%-0.40%; boron (B): 0.003%-0.02%; nitrogen (N): 0.0%-0.40%; titanium (Ti): 0.02%-0.10%; vanadium (V): 0.10%-0.30%; niobium (Nb): 0.02%-0.08%; copper (Cu): 1.20%-2.10%; and aluminum (Al): 0.003%-0.06%, in particular 0.005%-0.04%; the remainder being iron (Fe).

Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

Abstract: A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.

Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

Abstract: A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.

Abstract: An alloy which includes at least the following (in % by weight): carbon (C): 0.15%-0.25%; silicon (Si): 0.0%-0.08%; manganese (Mn): 0.03%-0.20%; chromium (Cr): 9.5%-10.5%; molybdenum (Mo): 0.4%-1.0%; tungsten (W): 1.6%-2.4%; cobalt (Co): 2.5%-3.5%; nickel (Ni): 0.0%-0.40%; boron (B): 0.003%-0.02%; nitrogen (N): 0.0%-0.40%; titanium (Ti): 0.02%-0.10%; vanadium (V): 0.10%-0.30%; niobium (Nb): 0.02%-0.08%; copper (Cu): 1.20%-2.10%; and aluminum (Al): 0.003%-0.06%, in particular 0.005%-0.04%; the remainder being iron (Fe).

Abstract: A rotor, in particular a gas turbine rotor, having multiple rotor discs, each of which has an axial through-opening, and the rotor discs are axially clamped by at least one tie rod extending through the through-openings and are combined so as to form at least one rotor disc unit. At least one support ring which surrounds the tie rod and is in engagement with a paired rotor disc rests against the outer diameter of the tie rod, and the tie rod is supported against the rotor disc by the support ring. In order to axially secure the at least one support ring, at least one securing ring is provided which is secured to the paired rotor disc by a rotational lock and which holds the support ring against the rotor disc. The securing ring is prevented from unscrewing by a securing plate.

Abstract: An annular clamping nut which is provided for being placed onto the end of a tie bar, in order to brace the latter, and which has in addition to a central recess for receiving the tie bar parallel to a longitudinal direction passages at uniform radial spacings in the ring circumferential direction which are directed parallel to the longitudinal direction of the central recess and are provided for receiving clamping screws. An external thread is provided on the outer surface of the clamping nut, which outer surface is arranged on a side which lies substantially opposite the wall of the central recess, which external thread runs substantially in the ring circumferential direction of the outer surface.

Abstract: A wheel disk assembly having a wheel disk, a plurality of blade devices, which are arranged thereon in a manner distributed over the circumference, and a plurality of sealing plates, which are retained in two annular grooves spaced apart from each other radially. In this assembly, the first annular groove is provided in the wheel disk and is bounded axially outward by an annular projection. The projection, in turn, is interrupted by a recess extending in the circumferential direction, with the result that a sealing plate can be inserted axially through the recess between the annular grooves. A closure piece is furthermore provided for closing the recess, which closure piece is captively retained on the sealing plate by a form fit.

Abstract: An iron-based steel comprising at least (in wt. %): carbon (C): 0.01%-0.10%; silicon (Si): 0.02%-0.7%; manganese (Mn): 0.3%-1.0%; chromium (Cr): 8.0%-10%; molybdenum (Mo): 0.1%-1.8%; cobalt (Co): 0.8%-2.0%; nickel (Ni): 0.008% -0.20%; boron (B): 0.004% -0.01%; nitrogen (N): 0.03% -0.06%; vanadium (V): 0.1% -0.3%, particularly 0.15% -0.022% of vanadium (V), more particularly 0.185% of vanadium (V); niobium (Nb): 0.01% -0.07%; optionally tungsten (W): 2.0% -2.8%, particularly 2.4% of tungsten; the remainder being iron (Fe); wherein said steel consists in particular of these elements.

Abstract: A steel having the following composition: carbon: 0.08%-0.12%, preferably 0.10%; silicon: 0.04%-0.08%; manganese: 0.08%-0.012%; chromium: 9%-II%; molybdenum: 0.4%-1.0%; tungsten: 1.6%-2.4%; cobalt: 2.5%-3.5%; nickel: 0.10%-0.24%; boron: 0.006%-0.01%; nitrogen: 0.002%-0.01%; titanium: 0.008%-0.03%; vanadium: 0.015%-0.029%; niobium: 0.03%-0.07%; optionally copper: 1.00%-2.5%; aluminum: 0.04%-0.10%; the remainder being iron, wherein said steel has improved properties, since no further Z-phase formation occurs.

Abstract: Wheel disc arrangement has a wheel disc, a plurality of blade devices fastened along the outer circumference, and a plurality of sealing plates held in two radially spaced-apart annular grooves. The first annular groove is bounded axially outwards by an annular projection. The second annular groove is defined by a plurality of adjacently arranged annular groove segments in the individual blade devices. The first annular groove is of undercut design and has at least two axially opposite and protruding holding projections with a respective bearing surface. The sealing plates have, in the inside diameter, two supporting projections corresponding to the holding projections, axially opposite and face away from one another, with a supporting surface. The arrangement is configured such that the supporting surfaces of the sealing plates are supported against the bearing surfaces of the holding projections under the effect of a centrifugal force.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rotor interior. For improved temperature control of the rotor disk, the holes conduct the medium through the rotor disk counter to the flow direction in the compressor.

Abstract: A rotor disk arrangement having a rotor disk which has, distributed around the outer circumference, a plurality of axially extending blade holding grooves and an encircling fastening protrusion and/or a plurality of fastening protrusions arranged in a circumferentially distributed manner, and having a plurality of sealing elements arranged in a circumferentially distributed manner, the sealing elements covering the blade holding grooves at least in portions on the end side and having, on the side facing the rotor axis, at least one fastening portion that bears against the underside of the fastening protrusion, wherein the fastening protrusion is embodied in an undercut manner, wherein the distance thereof from the rotor axis at the free end facing away from the rotor disk is less than in a region within the fastening protrusion.

Abstract: A rotor for a turbine has a plurality of rotor components lined up in the axial direction and connected by a connecting rod, wherein a groove which extends in the circumferential direction and is open in the axial direction is disposed on one of the rotor components, wherein a coupling element running around the connecting rod in order to support the connecting rod is disposed in the groove. The rotor is adapted to enable particularly stable support of the connecting rod in order to prevent vibrations. The coupling element is disposed on a retaining element connected to the connecting rod.

Abstract: An arrangement for securing a functional position of a shroud plate of a rotor of a gas turbine, which shroud plate is arranged on an outer circumference of a rotor disc of the rotor, relative to a moving blade of the rotor arranged on the outer circumference of the rotor disc, wherein a channel portion of an annular cooling channel of the rotor is formed between the shroud plate located in its functional position and a side, facing the shroud plate, of a blade root of the moving blade. A rotor assembly for a rotor of a gas turbine, having a rotor disc, a moving blade ring arranged on the outer circumference of the rotor disc and a shroud plate ring arranged on the outer circumference of the rotor disc.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.

Abstract: A sealing system includes a bolt and a cover plate for sealing a joint between a rotor disk and a blade root of a rotor blade, the blade root being disposed in a blade root slot in the rotor disk. The sealing arrangement is used in particular in a gas turbine.