Siemens Aktiengesellschaft

Mtu Aero Engines Gmbh

Matthias Oechsner

Volker Vosberg

Ursula Pickert

Dirk Goldschmidt

Georg Bostanjoglo

Tobias Buchal

Jan Münzer

Ralf Müsgen

Rudolf Küperkoch

Thorsten Mattheis

Winfried Eβer

Torsten Koch

Katharina Bergander

Eckart Schumann

Alexander Ralph Beeck

Michael Ott

Werner Stamm

Robert Singer

Jan Steinbach

Winfried Esser

Uwe Paul

Andreas Volek

Michael Dankert

Stefan Irmisch

Martin Feldhege

Thomas Malow

Beate Seiler

A pyrochlore ceramic material and a thermal barrier coating containing pyrochlore ceramic materials are provided. Using the thermal barrier coating in a single or double layer which includes magnesium and/or titanium can improve the spallation behavior and the thermal expansion coefficient of the component onto which the thermal barrier coating is applied.

Pyrochlore materials and a thermal barrier coating with these pyrochlore materials

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 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 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

Method for recording microstructural changes in a layer system component. A specific material parameter of the component is measured. The layer system may include an alloy substrate and an alloy or porous ceramic layer. The material parameter may be measured a plurality of times. The measured material parameter may include electrical capacitance, specific heat capacity, peltier coefficient or magnetic susceptibility. The material parameter may first be measured on a new component and subsequent measurements may be performed at a time interval after operational use. The recorded material parameter is then used to determine microstructural changes in the substrate or the layer material of the component caused by changes in precipitation, cracks, or depletion of an alloying element.

Method for recording microstructural changes in a component

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Mülheim an der Ruhr, Germany

Matthias Oechsner