Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is designed to conduct a medium, such as compressor air, in the interior of the gas turbine. In order to conduct the medium in the interior with low flow losses and at the same time to specify a rotor that can be produced comparatively simply and economically, a separately produced blade wheel is arranged between the mutually adjacent hub regions of the two rotor discs. The first side of said blade wheel lies against the hub region of the second rotor disc and the second side opposite the first side has a number of ribs, which extend from radially outside to radially inside.

Abstract: A rotor disk of a rotor, in particular of a gas turbine, which has serrations, at least on one side, for torque transmission, having a plurality of teeth distributed over the circumference, the tooth flanks of which are aligned opposite with respect to a respective central plane, wherein the tooth flanks have a course that deviates from a radial direction in a cross section perpendicular to the rotor axis.

Abstract: A wheel disk assembly, having a wheel disk, a plurality of blade devices, which are fastened along the outer circumference of the wheel disk, and a plurality of sealing plates, which are retained in two annular grooves radially spaced apart from each other. A first annular groove is in the wheel disk and a second annular groove is formed by the blade devices in a segmented manner. Simplified mounting of the sealing plates is achieved in that the first annular groove is expanded by an axially extending recess.

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: 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 wheel disc arrangement having a wheel disc, having multiple vane devices which are fastened along an outer circumference of the wheel disc, having at least one sealing plate received between the wheel disc and the vane devices so as to be displaceable in a circumferential direction, and having at least one securing device designed so as to secure the sealing plate against a displacement in the circumferential direction, wherein the securing device has a bolt, which extends through a passage opening provided in the sealing plate, and a recess, which is provided on the wheel disc or on a vane device, which recess receives the free end of the bolt and the wall of which recess limits a movement of the bolt in the circumferential direction, wherein the bolt is, in an axial direction, secured on the sealing plate against undesired release by way of a detent connection.

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: 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 wheel disc with at least one sealing metal sheet, which is fixed to the wheel disc in a movable manner in the circumferential direction of the wheel disc, and with at least one securing device, which is designed to secure the at least one sealing metal sheet against a displacement in the circumferential direction of the wheel disc in the correctly assembled state. The securing device has a screw, which is screwed to the sealing metal sheet and which extends through the sealing metal sheet, and a depression, which is provided on the wheel disc and which receives the free end of the screw in the correctly assembled state and the wall of which restricts a movement of the screw in the circumferential direction.

Abstract: A rotor, in particular a gas turbine rotor, having a plurality of rotor disks which each have an axial through-opening and which are axially tensioned by at least one tension rod which extends through the through-openings and which are combined to form at least one rotor disk unit, wherein there abuts the outer diameter of the tension rod at least one support ring which is in engagement with one of the rotor disks and via which the tension rod is supported on the rotor disk. At least one securing element is provided for axially securing the at least one support ring. The securing element is fixed to the rotor disk to which the support ring is connected and is constructed such that it engages round an end face of the support ring, which face is directed away from the rotor disk.

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 fastened along the outer circumference of the wheel disk, and a plurality of sealing plates, which are retained in two annular grooves radially spaced apart from each other, the first annular groove in the wheel disk and bounded axially outward by an annular projection, and the second annular groove defined by a plurality of annular-groove segments arranged adjacently, which are in the individual blade devices. At least one opening extends axially through the annular projection, the minimum width of which opening in the circumferential direction is greater than the width of the sealing plates at the inside diameter such that a sealing plate is axially insertable between the annular grooves through the opening and moveable in the circumferential direction while guided by the annular grooves. A method assembles such a wheel disk assembly.

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.

Abstract: A turbine blade with a turbine blade aerofoil, a turbine blade root and a turbine blade platform located between the turbine blade aerofoil and the turbine blade root and having, in its underside, an insertion groove for the insertion of a sealing plate; the sealing plate can be secured by a securing element supported on the turbine blade platform, and the turbine blade platform has a material cut-out with two support edges located opposite each other in such a way that the securing element can be secured on both sides to the turbine blade across the axial extension of the turbine blade root.

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: 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, designed to conduct a medium, such as compressor air, in the interior of the rotor. In order to conduct the medium in the interior with low flow losses and at the same time to specify a rotor that can be produced comparatively simply and economically, a separately produced blade wheel is arranged between the mutually adjacent hub regions of the two rotor disks, and a sleeve is provided for fastening the blade wheel to one of the two rotor disks, which sleeve extends through the central opening of the one rotor disk and includes a collar serving as a stop at a first end of the sleeve and includes a second end opposite the first end, on which second end the blade wheel is fastened.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is designed to conduct a medium, such as compressor air, in the interior of the gas turbine. In order to conduct the medium in the interior with low flow losses and at the same time to specify a rotor that can be produced comparatively simply and economically, a separately produced blade wheel is arranged between the mutually adjacent hub regions of the two rotor discs. The first side of said blade wheel lies against the hub region of the second rotor disc and the second side opposite the first side has a number of ribs, which extend from radially outside to radially inside.

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 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.