Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Mtu Aero Engines Gmbh

Volker Vosberg

Tobias Buchal

Ursula Pickert

Matthias Oechsner

Dirk Goldschmidt

Georg Bostanjoglo

Jan Münzer

Ralf Müsgen

Thorsten Mattheis

Rudolf Küperkoch

Torsten Koch

Winfried Eβer

Katharina Bergander

Dieter Minninger

Brigitte Heinecke

Alexander Ralph Beeck

Fathi Ahmad

Michael Ott

Robert Singer

Eckart Schumann

Mirko Milazar

Matthias Heue

Silke Settegast

Claus Krusch

Jan Steinbach

Winfried Esser

Arnd Reichert

Nihal Kurt

Uwe Paul

Andreas Volek

Stefan Dahlke

Harald Nimptsch

Bernd Stöcker

Heinrich Pütz

Kang Qian

Martin Lenze

Uwe Gruschka

Axel Schaberg

Stephan Schmidt

Steffen Skreba

Christian Menke

Gerhard Hülsemann

Michael Neubauer

Hajrudin Ceric

Thomas Matern

Roger Waldinger

Raoul Galic

Margarete Neuhaus

Beate Seiler

A guide vane ring which is divided into an upper and into a lower guide vane ring half, with an inner ring which is split at least in two, has a substantially U-shaped cross section, and forms a radially outwardly open flow duct which extends in the circumferential direction and is delimited by way of an inner ring bottom wall and two inner ring side walls, and with a multiplicity of vane platforms which receive guide vanes, are arranged along the outer circumference of the inner ring, and have holding webs which in each case project radially inwards, are spaced apart from one another in the axial direction, and engage around the inner ring side walls from the outside, wherein wear elements are inserted into gaps which are present between holding webs and directly adjacently arranged inner ring side walls.

Guide vane ring with wear elements

Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Gas turbine for a thermal power plant, and method for operating such a gas turbine

A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Gas turbine with a guide vane

The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

A method for repairing wider gaps in a substrate of a component by brazing at a brazing temperature is provided. Filler material and solder are prevented from separating in that, in a two-stage process, first the filler material and then the solder are applied to the wider gap. The powder does not melt at the brazing temperature and the filler metal does melt at the brazing temperature.

Process for brazing wide gaps

A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.

Turbine blade for a turbine with a cooling medium passage

The invention relates to a method for repairing components comprising a base material with an oriented microstructure, wherein the repair point comprises a correspondingly oriented microstructure as the surrounding base material. According to the inventive method, solder is applied in the region of a point which is to be repaired and is soldered to the component by means of a heating effect produced by a device. A temperature gradient, i.e., approximately a temperature characteristic, is produced during the heating effect, said temperature characteristic ranging from a high to a low temperature in the region of the point which is to be repaired.

Repair soldering method for repairing a component which comprises a base material with an oriented microstructure

A brazing composition for the brazing of superalloys including a base material with at least one initial phase is provided. The initial phase has a solidus temperature that is below the solidus temperature of the base material and, above a certain temperature, forms with the base material and/or with at least one further initial phase at least one resultant phase, the solidus temperature of which is higher that the solidus temperature of the initial phases. Heat treatment takes place in two stages, wherein the temperature of the second heat treatment is preferably 800-1200&#xb0; C. The brazing composition may likewise be of the type MCrAlX, and the power particles of the initial phase may be in the form of nanoparticles.

Brazing composition and brazing method for superalloys

A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. In the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.

Turbine blade

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

The invention proposes a cooling system () for a gas turbine (), with an annular duct extending axially in the compressor (). In the annular duct, a ring () of compressor guide blades () and a ring () of moving blades () fastened to a rotor disk () of the rotor () are provided, with at least one cooling-air extraction point (), arranged on the rotor (), for diverting a cooling-air stream into a cooling-duct system arranged in the rotor (), and with a turbine unit (), in which, when the gas turbine () is in operation, components subjected to thermal stress by a hot gas () can be cooled by the divertible cooling-air stream, and also with a feed line () for feeding a liquid () into the cooling-air stream. In order to make it possible to feed a liquid into the cooling-air stream simply and cost-effectively, the invention proposes that the feed line () extend with a subduct () through at least one of the compressor guide blades () of the ring (), and the orifice () for the outlet of the liquid () be connected in the region of the cooling-air extraction point ().

Cooling system for a gas turbine

Growing community of inventors

Mülheim an der Ruhr, Germany

Volker Vosberg