Siemens Aktiengesellschaft

Oliver Schneider

Peter Schröder

Francois Benkler

Joachim Krützfeldt

Silvio-Ulrich Martin

Vyacheslav Veitsman

Ulrich Waltke

Nicolas Savilius

Uwe Kahlstorf

Fathi Ahmad

Andreas Böttcher

Karsten Kolk

Marc Tertilt

Harald Hoell

Mirko Milazar

Tobias Buchal

Winfried Esser

Sascha Dungs

Matthias Hase

Christoph Hermann Richter

Ralf Müsgen

Marco Larson

Dieter Minninger

Daniel Grundei

Rudolf Küperkoch

Ulrich Ehehalt

Walter Loch

Norbert Thamm

Birgit Grüger

Markus Kunze

Kang Qian

Stefan Mutke

Michael Schwarz

Peter-Andreas Schneider

Harald Nimptsch

Marco Link

Philipp Kreutzer

Gerhard Simon

Guido Ahaus

Martin Hartmann

Martin Stapper

Vadim Shevchenko

Markus Gill

Shilun Sheng

Dirk Wistuba

Oliver Lüsebrink

Torsten Matthias

Roderich Bryk

Uwe Lohse

Hans-Georg Gamm

Frank Deister

Karl Klein

Thomas Kerstiens

Carsten Kaufmann

Scarlett Fajardo-Reina

Jörn Bettentrup

Stefan Werner Kiliani

Ekkehard Maldfeld

Achim Schirrmacher

Jan-Dirk Beiler

Rosa-Eos Mühlhölzer

Richard Graefe

Florian Purps

Rafael Labisch

Marc Schäfer

Marc Reinberg

Waldemar Socha

Marc SCHÄFER

Andre Botzen

Rafael Labish

A machine having a shaft with a stage having a first shaft section having a first diameter, a second shaft section having a second diameter that is shorter than the first, forming a radially extending rotatable shaft end surface; a housing; and a bearing supporting the shaft on the housing by its second shaft section, and lubricated by a lubrication fluid. A sealing chamber has a sealing fluid that prevents the lubrication from leaving the bearing, and is axially limited by the shaft end surface and bearing end side, and radially inwardly limited by the second shaft section released from the bearing. A radially extending and stationary separator plate is in the sealing chamber to achieve an aerodynamic shielding of the bearing end side from the shaft end surface. When the shaft is rotating, the region between the separator plate and the bearing end side is substantially non-rotational.

Machine and method for operating the machine

A method for operating a gas turbine plant having a gas turbine and an electric generator driven by the gas turbine. The method includes detecting an instantaneous power of the gas turbine plant; comparing the detected instantaneous power with a power limit value; and limiting the instantaneous power when the result of the comparison is that the detected instantaneous power is equal to or greater than the power limit value. A step of detecting at least one operating parameter of the gas turbine plant and a step of determining the power limit value as a function of the at least one detected operating parameter are then implemented, wherein the at least one operating parameter of the gas turbine plant includes an ambient pressure and the power limit value is increased when the ambient pressure increases.

Variable power limit control for gas turbines

An ambient air intake duct of a static gas turbine is provided, having at least one filter, which is arranged in the intake duct, for cleaning the ambient air (A) that can flow through the intake duct. A method for operating a static gas turbine which is equipped with a filter for cleaning the ambient air (A) is also provided. To rapidly provide a higher level of gas turbine power to a generator, it is provided that, by means of a bypass or by means of flaps arranged downstream of the filter, partially to completely unfiltered ambient air (A) can temporarily flow into the compressor inlet.

Method for operating a static gas turbine, and intake duct for intake air of a gas turbine

An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.

Axial turbomachine having an axially displaceable guide-blade carrier

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

A passage wall section of an annular flow passage of an axial turbomachine is provided. A guide ring has a first toothing arrangement which is in contact with a second toothing arrangement arranged on a sidewall of a circumferential groove which accommodates the guide ring, wherein for axial displacement of the displaceable guide ring, the guide ring is rotatable in a circumferential direction.

Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment

A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Rotor of a gas turbine

A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Turbomachine rotor comprising a pretensioning device for pretensioning a rotor blade

A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.

Turbine blade

A closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery is provided. The assembly includes at least two parts each of which can be hooked onto projections that form an undercut in the peripheral groove and includes a securing element, which secures the parts from becoming detached from the peripheral groove. For closing the remaining gap, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web can be positioned by rotation is such a way that to fit the parts in the peripheral groove. The parts can be displaced in relation to one another and to secure the parts from being detached from the groove. The web can be placed against at least one lateral face of one of the parts.

Closing assembly for a blade ring of turbomachinery

A closing assembly is provided. The closing assembly closes the gap remaining between the first blade and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, the assembly consisting of at least two lateral parts, at least one of which may be hooked onto a projection that forms an undercut in the peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit.

Locking sub-assembly for closing the remaining gap between the first and the last of a blade ring which are inserted in a circumferential groove of a turbomachine, and corresponding turbomachine

Growing community of inventors

Wesel, Germany

Oliver Schneider