Abstract:
A sealing washer for use in a rotor of a gas turbine, sealing being brought about on one side of the sealing washer by an approximately radially oriented bearing face and on the other side by way of a supporting face which is oriented in an inclined manner with respect to the rotor axis. The sealing washer is of split configuration and has at least one washer segment with a circumferential washer section. At the dividing point, a pressing section and a triangular section overlap along a dividing face. Here, the dividing face intersects the bearing face and makes sealing both with the pressing section and with the triangular section possible. In order to also make sealing on the supporting face with the pressing section and the triangular section possible, the triangular section is reduced to at most 0.3 times the cross-sectional area of the washer section.
Abstract:
A wheel disk assembly having a wheel disk, a plurality of blade devices fastened along an outer circumference of the wheel disk, a plurality of sealing plates accommodated between the wheel disk and the blade devices such that the sealing plates are moveable in the circumferential direction, and securing devices designed such that the securing devices secure the sealing plates against movement in the circumferential direction. Pins are provided as securing devices, which pins are detachably retained in bores arranged on the wheel disk and reach into recesses that are formed on surfaces of the sealing plates facing the wheel disk, wherein at least one of the pins, preferably all of the pins, are designed such that, in order to disengage a pin from the associated recess, the pin in question can be plunged further into the bore in a resilient manner.
Abstract:
An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.
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 rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width 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:
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 gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.
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:
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.