Siemens Aktiengesellschaft

Rudolf Küperkoch

Georg Bostanjoglo

Tobias Buchal

Volker Vosberg

Jan Münzer

Ralf Müsgen

Ursula Pickert

Matthias Oechsner

Thorsten Mattheis

Dirk Goldschmidt

Winfried Eβer

Torsten Koch

Katharina Bergander

Thomas Beck

Alexander Ralph Beeck

Andreas Böttcher

Eckart Schumann

Oliver Schneider

Winfried Esser

Giuseppe Gaio

Francois Benkler

Nicolas Savilius

Christian Amann

Rostislav Teteruk

Dirk Wistuba

Björn Beckmann

Frank Deister

Jörn Bettentrup

Thorsten Koch

A layer system including a substrate and a layer is provided. The layer system has a hole at least in the layer, and wherein at least one recess is present in a surface of the layer in a vicinity around the hole or directly adjoining a boundary line of the hole.

Modified interface around a hole

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 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

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

Growing community of inventors

Essen, Germany

Rudolf Küperkoch