Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Mirko Milazar

Karsten Kolk

Harald Hoell

Sascha Dungs

Peter Schröder

Vyacheslav Veitsman

Tobias Buchal

Axel Buschmann

Guido Ahaus

Peter Tiemann

Fathi Ahmad

Andreas Böttcher

Christopher W Ross

Holger Grote

Volker Vosberg

Oliver Schneider

Kevin Kampka

Winfried Esser

Giuseppe Gaio

Arnd Reichert

Christian Lerner

Dieter Minninger

Francois Benkler

Daniel Grundei

Peter Kury

Bernd Vonnemann

Nicolas Savilius

Uwe Kahlstorf

Björn Buchholz

Harald Nimptsch

Thomas-Dieter Tenrahm

Birgit Grüger

Norbert Thamm

Vadim Shevchenko

Gerhard Simon

Daniel Hofsommer

Martin Hartmann

Heinrich Pütz

Roderich Bryk

Kang Qian

Oliver Lüsebrink

Shilun Sheng

Yulia Bagaeva

Markus Raben

Kunyuan Zhou

Uwe Lohse

Andreas Föhrigen

Thomas Hille

Karl Klein

Gerhard Hülsemann

Michael Neubauer

Ekkehard Maldfeld

Alfred Lienert

Ivan Lbov

Alexander Romanov

Rene Mahnke

Stefan Wanjura

Matthew Gent

Patrick M Ritchie

Jörg Richter

Andreas Andreas

Friedhelm Terschuren

Mathias Stutt

Anna Kapustina

Eric Schwerin

Waldemar Socha

A flat shaped sealing device for sealing a gap between two parts having a sealing length and a sealing width from one side edge to the opposite side edge of at most 0.2-times the sealing length and having a sealing thickness from a bottom side to a top side of at most 0.2-times the sealing width. The sealing device includes a head section and an adjacent main section. The head section includes an abutment and a spring, wherein the abutment is displaceable towards the main section and the spring is therefore arranged between the abutment and the main section and is able to exert a force on the abutment.

Sealing device with displaceable abutment

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.

Rotor comprising a rotor component arranged between two rotor discs

A sealing element for sealing a gap between two components is provided. The sealing arrangement may be a seal arrangement of a gas turbine system, wherein the sealing element is elongate along a main line and has a contoured cross section in a corrugated center region. In cross section, the sealing element is directed along the main line and may be deformed in a direction substantially orthogonally with respect to the main line. In order to provide a wear-resistant, long-lasting sealing element with a particularly efficient blocking action, it is proposed that the seal teeth of the corrugation have a virtually rectangular cross-sectional contour, the tooth height of which seal teeth is between 10% and 40% of the sealing-element thickness which may be measured parallel to the tooth height.

Sealing element for sealing a gap

A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.

Guide vane system for a turbomachine having segmented guide vane carriers

A method for measuring and adjusting gaps between a rotor and a stator of a machine using a sensor is provided. The measuring is conducted when the rotor is operated at a rotational speed below a nominal rotational speed of the machine and without the machine being in operation. The adjusting of the gap is carried out as a function of at least one gap dimension of the gap. The sensor is not resistant to an operating temperature of the machine occurring in a region where the sensor is located. After completion of the measuring the machine is operated with the sensor.

Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall

A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.

Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine

A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face.

A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety.

Axially segmented guide vane mount for a gas turbine

The invention relates a method for improving the hot-starting behavior of a turbomachine. By virtue of the setting of a radial gap formed between a brushing edge of a blade profile and a guide face lying opposite this, in which setting a guide ring forming the guide face can be acted upon with a coolant, the hot-starting behavior can be improved, in that the guide ring is cooled before the start of the machine.

Method for setting a radial gap of an axial-throughflow turbomachine and compressor

A gas turbine, with a fixed inner housing, arranged concentric to the rotor, with a through flow of working medium, is disclosed. The housing comprises at least two serial rings with an annular gap left between two directly adjacent rings, whereby an annular sealing means is arranged in at least one peripheral groove for sealing the annual gap. According to the invention, a sealing means is provided which permits a greater movement of both components forming the gap, whereby the annual gap is formed by partly overlapping rings, running against the flow direction of the working fluid in the radial sense and the front most of the two rings, in the sense of the flow direction, comprises a locating annular surface for the sealing means embodied as an annular spring element on which the spring element rests under tension such as to seal the annular gap.

Gas turbine and sealing means for a gas turbine

Method of minimizing the gap between a wheel and a casing of a turbine, a turbine, and a method of determining the wear behavior of a wheel of a rotor. To minimize the gap between a wheel and a casing in a turbine, optical methods are also often used in order to minimize the gap. However, this is very expensive. The method according to the invention proposes that the wheel and the casing (be part of an electric circuit, so that an electrical parameter, such as resistance for example, can be measured, the value of which shows whether a contact is present.

Method of minimizing the gap between a rotating turbine blade and a casing of a turbine, a turbine, and a method of determining the wear behavior of a wheel of a rotor

A gas turbine includes a first turbine stage having a first guide blade, a first moving blade and a cooling configuration. The cooling configuration has a first cooling-air feed at the first guide blade for cooling the first guide blade, a first cooling-air supply at a first pressure for supplying the first cooling-air feed, and a second cooling-air feed disposed downstream of the first cooling-air feed for cooling the first guide blade. The second cooling-air feed is supplied with a second pressure lower than the first pressure.

Gas turbine having a turbine stage with cooling-air distribution

A sealing element seals a gap which may be formed between two components that are movable thermally relative to one another. Each component has a component groove located one opposite the other. The sealing element is directed along a center line, in a cross-section essentially perpendicular to a main line, and has a first end, a second end located opposite the first end and a toothed middle region located between the ends. The sealing element is suitable in particular for sealing off a gap between guide blades at high temperatures in a gas turbine plant for the purpose of preventing a gas flow out of a cooling-gas region into a hot-gas region. A gas turbine plant is provided with the sealing element for sealing the gap.

Sealing element for sealing a gap and gas turbine plant

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Oberhausen, Germany

Mirko Milazar