Siemens Aktiengesellschaft

Harald Nimptsch

Karsten Kolk

Harald Hoell

Tobias Buchal

Peter Schröder

Fathi Ahmad

Bernd Prade

Douglas J Arrell

Vyacheslav Veitsman

Mirko Milazar

Volker Vosberg

Oliver Schneider

Michael Huth

Arnd Reichert

John Carl Glessner

Dieter Minninger

Francois Benkler

Ulrich Ehehalt

Walter Loch

Peter-Andreas Schneider

David W Hunt

Heinrich Pütz

Guido Ahaus

Kang Qian

Werner Setz

Sven Bethke

Reimar Schaal

Gerhard Hülsemann

Michael Neubauer

Hans-Jürgen Kiesow

A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening.

Cooling of a gas turbine component designed as a rotor disk or turbine blade

A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Rotor of a gas turbine

A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.

Rotor for an axial flow turbomachine

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

A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Combustion chamber for a gas turbine with at least two resonator devices

Growing community of inventors

Essen, Germany

Harald Nimptsch