Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Christian Lerner

Fathi Ahmad

Marc Tertilt

Hans-Thomas Bolms

Holger Grote

Eckart Schumann

Mirko Milazar

Jens Kleinfeld

Christian Cornelius

Michael Händler

Giuseppe Gaio

Knut Halberstadt

Ralf Müsgen

Reiner Anton

Thorsten Mattheis

Stefan Baldauf

Kay Krabiell

Bernd Vonnemann

Thomas-Dieter Tenrahm

Rostislav Teteruk

Björn Anders

Uwe Gruschka

Silvio-Ulrich Martin

Stefan Braun

Thomas Hofbauer

Olaf Hein

Knut Haberstadt

Beate Seiler

Mathias Stutt

Adam Zimmermann

Andreas Heilos

Andreas BÖTTCHER

Annika Emde

A turbine blade tip, turbine blade and method where improved cooling is made possible by an improved cooling structure with cooling air holes inside a depression in a blade tip and a special arrangement of multiple cooling air holes which are supplied by a single cooling air channel inside a wall.

Turbine blade tip, turbine blade and method

A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.

Guide vane system for a turbomachine having segmented guide vane carriers

A process for setting the average flow rate within a hollow component is provided. The process includes setting a relatively small wall thickness in a first region with a relatively large flow cross section using a first diffusion coating process and setting a relatively large wall thickness by a second different diffusion process in a second region with a relatively small flow cross section. The use of different diffusion coatings in a component allows the flow of coolant through a component to be set in a controlled manner.

Method for assessing the coolant consumption within actively cooled components

A method for adjusting the coolant consumption within actively cooled components is produced. The components include an interior with at least one duct with different regions which have different cross sections of flow. A greater increase in the wall thickness is produced in the region having the smaller cross section of flow by a first diffusion process and a lesser increase in the wall thickness is produced in the region having the larger cross section of flow by a second diffusion process which is different from the first. By using different diffusion coatings in a component, it is possible to adjust the flow of coolant through a component in a controlled way.

Method for adjusting the coolant consumption within actively cooled components, and component

A turbine blade is presented including a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. An improved cooling of a platform region and the transition region is provided from a turbine blade to a platform of a turbine blade. The platform includes a first platform wall that does not support the vane and a second platform wall that supports the vane. At the root of the vane and over the course of the transition region from the turbine blade to the platform, the first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.

Turbine blade and gas turbine equipped with a turbine blade

The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

There is described a turbine blade of a gas turbine comprising a suction-side blade wall and a pressure-side blade wall that, in the trailing edge area, runs toward the suction-side blade wall. This suction-side blade wall has a trailing edge projection projecting over the end edge of the pressure-side blade wall at least in a partial section of the trailing edge area. A turbine blade of the aforementioned type is designed for a particularly long serviceable life while requiring little cooling air. To this end, the pressure-side surface of the trailing edge projection has a number of trough-shaped recesses that increase the transfer of heat from the trailing edge projection by a local swirling of the cooling air.

Turbine blade for a gas turbine, use of a turbine blade and method for cooling a turbine blade

The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

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Herten, Germany

Christian Lerner