Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Thorsten Mattheis

Georg Bostanjoglo

Tobias Buchal

Volker Vosberg

Jan Münzer

Ursula Pickert

Ralf Müsgen

Matthias Oechsner

Rudolf Küperkoch

Winfried Eβer

Katharina Bergander

Alexander Ralph Beeck

Fathi Ahmad

Eckart Schumann

Winfried Esser

Christian Cornelius

Dirk Goldschmidt

Torsten Koch

Martin Schäfer

Radan Radulovic

Christian Lerner

Daniela Koch

Rostislav Teteruk

Silvio-Ulrich Martin

Thomas Hofbauer

Stefan Braun

Olaf Hein

Markus Lempke

Christian Menke

Sören Fenske

Axel Podschwadek

Anne Weidenmüller

Andreas Heilos

Horst-Michael Dreher

Adam Zimmermann

Annika Emde

Thorsten Koch

A production method for a component having integrated channels for internal fluid guidance, having a first region, which is connected to a second region, and wherein the channels extend both through the first region and through the second region. The geometry of the component is modified to the technological characteristics of both production methods. The first region is produced by a method for casting using lost models without undercuts, and proceeding from the first region, the second region is built up using an additive manufacturing method.

Production method for a component having integrated channels and component

A method for producing a cavity in a blade platform of a blade, in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bore from a first platform lateral face in the direction of an opposite second platform lateral face, with a first opening in the first platform lateral face being created, and expanding the first bore in a fan-like manner by an electrical discharge machining method, in particular using a wire- or bar-form electrode, such that the first opening, created in the first step, of the first bore represents the starting point of the fan-like expansion. A blade is produced in particular with such a method.

Method for producing a cavity in a blade platform; corresponding 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

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Mülheim, Germany

Thorsten Mattheis