Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesell Schaft

Peter Schröder

Karsten Kolk

Vyacheslav Veitsman

Kevin Kampka

Harald Hoell

Sascha Dungs

Oliver Schneider

Christopher W Ross

Dirk Springborn

Christian Kowalzik

Francois Benkler

Joachim Krützfeldt

Axel Buschmann

Guido Ahaus

Fathi Ahmad

Andreas Böttcher

Mirko Milazar

Christoph Hermann Richter

Nihal Kurt

Dieter Minninger

Ulrich Waltke

Uwe Kahlstorf

Michael Händler

Peter Kury

Stefan Schmitt

Markus Kunze

Christian Kowalski

Silvio-Ulrich Martin

Ching-Pang Lee

Kok-Mun Tham

Tobias Buchal

Winfried Esser

Sin Chien Siw

Ulrich Ehehalt

Nicolas Savilius

Martin Hartmann

Bernd Vonnemann

Walter Loch

Birgit Grüger

Björn Bilstein

Kang Qian

Yulia Bagaeva

Stefan Mutke

Marc Lange

Michael Schwarz

Karin Costamagna

Rostislav Teteruk

Oliver Lüsebrink

Torsten Matthias

Werner Setz

Roger Matthews

Peter-Andreas Schneider

Thomas-Dieter Tenrahm

Harald Nimptsch

Vadim Shevchenko

Stefan Braun

Marcus Brücher

Andreas Föhrigen

Reimar Schaal

Sabine Rintzel

Patrick M Pilapil

Hubertus Michael Wigger

Santiago R Salazar

Jürgen Hahn

Michael Neubauer

Bernd Van Den Toorn

Nicholas F Martin

Christoph Schiefer

Javan Albright

Dieter Kienast

Martin Raschnewski

Joachim Reisener

Ulf Laudage

Wilfried Remmert

James McCoy

Andrew Waddell

Werner Polanz

David Miosga

Ivan Lbov

Christopher Butzeck

Patricia Hülsmeier

Ekkehard Maldfeld

Joana Verheyen

Waldemar Socha

Andrew R Waddell

Andreas BÖTTCHER

A sealing ring for a turbomachine, having at least a first and a second segment. The first segment has, in a region of a first longitudinal end, a first recess and a first projection having a first flank which delimits the first recess. The second segment has, in a region of a second longitudinal end, a second recess and a second projection having a first flank which flank delimits the second recess. The first and second segments have a coupling state in which they are movable relative to one another. The first projection is arranged in the second recess, the second projection is arranged in the first recess, and the first flank of the first projection and the first flank of the second projection are designed to abut one another upon a first movement of the first segment away from the second segment and to limit the first movement.

Rotor and turbomachine comprising the rotor

A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.

Cover plate with flow inducer and method for cooling turbine blades

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.

Sealing washer for a rotor, and rotor with such a washer

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.

Rotor comprising a rotor component arranged between two rotor disks

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.

Rotor with centrifugally optimized contact faces

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.

Rotor with sealing element and ring seal

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.

Rotor with a locking plate for securing an antirotation lock against unscrewing

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.

Wheel disk assembly

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.

Wheel disk assembly having sealing plates

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.

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.

Rotor disk having an end-side sealing element

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.

Rotor for a turbine

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.

Arrangement for securing a functional position of a shroud plate arranged on a rotor disc relative to a moving blade arranged on the rotor disc

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.

Sealing system and gas turbine

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.

Rotor for a thermal turbomachine

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Essen, Germany

Peter Schröder