Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Bernd Vonnemann

Giuseppe Gaio

Marc Tertilt

Thomas-Dieter Tenrahm

Peter Schröder

Fathi Ahmad

Holger Grote

Mirko Milazar

Olga Deiss

Jens Kleinfeld

Christian Lerner

Christian Jäkel

Gilbert Braun

Martin Hartmann

Vadim Shevchenko

Rick Giesel

Kai-Uwe Rogos

Edmund Zastrozny

Marcus Fischer

Frank Günther

Sabine Rintzel

Andreas Heilos

Petros Terzis

Mathias Stutt

Michael Winterstein

Peter Schroeder

Katrin Linnemann

Maria De La Paz Mosquera Ruiz

Matthias Beutin

Holger Eisenlohr

Sonja Rehmann

Claudia Barbeln

Werner Polanz

Jannik Lüpfert

Claudia Alders

Thomas Tenrahm

Provided is a silo combustion chamber comprising a vertically extending flame tube that can be lit from above and through which circulation takes place in a downward motion, the outer surface of the flame tube being provided with a plurality of cooling fluid supply openings and the inside thereof being lined with ceramic heat shield elements, the lowest heat shield elements being supported on a metal supporting ring; a conically tapered mixing tube arranged downstream from the flame tube, into which the lower region of the flame tube is set; and an outer housing that surrounds the flame tube and the mixing tube, forming an annular supply channel, the lowest heat shield elements completely covering the radially inwardly oriented surfaces of the supporting ring. Also provided is a method for retrofitting a silo combustion chamber.

Silo combustion chamber and method for retrofitting same

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 retaining element for retaining a heat shield element on a support structure comprises at least one fixing section adapted to fix the retaining element to the support structure and at least one retaining section adapted to engage with an engaging groove present on a periphery of the heat shield element. A projection is arranged on the retaining element in such a manner that it projects in the direction of the heat shield element when retaining a heat shield element.

Retaining element and heat shield element for a heat shield and combustion chamber provided with a heat shield

The invention relates to a gas turbine, with a flow path for a hot gas, enclosed by a channel wall with at least one measuring probe, arranged in the channel wall, for determination of a parameter of the hot gas, said measuring probe comprising a temperature-resistant measuring tip in contact with the hot gas and a measuring line, arranged outside the flow path in a protective sleeve. According to the invention, such a gas turbine with a structurally uncomplicated protective sleeve for measuring lines from measuring probes, in which the measuring lines can be economically fitted and securely protected from excessively high operating temperatures, may be achieved, whereby the protective sleeve has a flow of coolant running therethrough which may be taken from a coolant supply connected to the protective sleeve.

Gas turbine with protective sheath for a probe and method for protecting an instrument lead which is laid in a protective sheath

A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

Heat shield

A device () for the demounting of blades (), which are pushed in with a blade root () on a wheel disk () of a blade wheel () of a turbine or of a compressor, is designed with a support () which is designed to be brought to bear against at least one component of the turbine, and is designed with an actuator () which is coupled to the support () and is designed for moving the blade root () mechanically out of the wheel disk ().

Device for the demounting of blades of a turbine or of a compressor

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Gladbeck, Germany

Bernd Vonnemann