Siemens Aktiengesellschaft

Tobias Krieger

Andreas Böttcher

Thomas Grieb

Timothy A Fox

Stephen A Ramier

Patrick Lapp

Ulrich Wörz

Daniel Vogtmann

Jens Kleinfeld

Andre Kluge

Jürgen Meisl

Peter Kaufmann

Werner Krebs

Claus Krusch

Matthias Hase

Olga Deiss

David M Ritland

Daniel W Garan

Christian Beck

Jaap Van Kampen

Torsten Jokisch

Birgit Grüger

Elmar Pfeiffer

Simon Purschke

Thomas Hauser

Sabine Tüschen

Holger Streb

Stefan Reich

Karsten Jordan

Udo Schmitz

Hartwig Dümler

Boris Ferdinand Kock

Mark F Rubio

Michael Neubauer

Kai-Uwe Schildmacher

Sabine Grendel

Christopher Grandt

Sascha Staring

Benjamin Witzel

Michael Winterstein

Marcus Zurhorst

Julia Mühl

Mariano Cano Wolff

Christin Schlensog

Ulrich WÖRZ

Andreas BÖTTCHER

Frank Wedekind

Youssef Moujane

Kaspar Matthias Malecha

Hartwig DÜMLER

Vasileios Papadopoulos

Alexander Nordalm

Andreas Mann

Shahrzad Juhnke

Dirk Mertens

Christopher Eckert

A heat shield with support structure and a number of heat shield blocks secured thereto, having a cold side facing the support structure and a hot side opposite the cold side. At least one recess is arranged in at least one heat shield block circumferential face, connecting the cold to hot side. An opening connecting the recess to the cold side runs in the circumferential face perpendicularly to the cold side. A securing bolt inserted into the opening secures the heat shield block to the support structure. A bolt head protrudes at least partly into the recess. The securing bolt passes through an angled plate having first limb extending substantially parallel to the circumferential face and second limb extending into the recess. The angled plate has a reinforcing device extending beyond the pure angular shape to increase a resistance of the angled plate against bending due to the securing bolt.

Securing a heat shield block to a support structure, and heat shield

A method for monitoring the operation of a gas turbine is provided, in which component vibrations are detected during the operation of the gas turbine by an acceleration sensor arranged on the component, a plurality of signal sections being determined by a plurality of frequency bands fb from the signal forwarded and processed by the acceleration sensor. To avoid an unnecessary shutdown of the gas turbine to perform an inspection which subsequently proves unnecessary, thereby increasing the availability of the gas turbine, a total vibration period is determined by adding together the vibration periods of signal sections during which the amplitudes of the signal sections concerned are greater than a frequency band-specific threshold.

Method for monitoring the operation of a gas turbine

A pipe connection that includes two tubular connection pieces for a conical clamping connection, the connection pieces being screwed together by a union nut while one connection piece is plugged inside the other. Each connection piece has a conical sealing surface which sealingly rests against the other, and an annular groove is provided in one of the sealing surfaces. The union nut is slit on the collar side.

Pipe connection for conducting a pressurized fluid

An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.

Gas turbine assembly and method therefor

A burner assembly is provided. The burner assembly includes a support housing with a supply manifold, the supply manifold includes a fuel passage system, and fuel nozzles extending from the supply manifold and being supplied with fuel through the fuel passage system of the supply manifold. The supply manifold is sandwiched using at least two subparts.

Burner assembly

A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided.

Burner, operating method and assembly method

A burner assembly having a fuel distribution ring, number of fuel nozzles which are mounted on the fuel distribution ring in the direction of low is provided. The fuel distribution ring has a ring-shaped surface in the direction of flow and wherein the fuel distribution ring center and an opposite outer outer side and wherein there is at least one slot on the surface between the fuel nozzles and the at least one slot extends on the surface from the outside to the inside. There is at least one recess arranged on the surface and the at least one recess also partially includes the outside of the fuel distributor.

Burner assembly including a fuel distribution ring with a slot and recess

A burner insert for a gas turbine combustion chamber is provided. The burner insert includes a burner insert wall including a cold side and a hot side, an edge delimiting the burner insert wall. The edge includes an edge bar extending at least partially circumferentially and projecting beyond the cold side. A burner opening for inserting a burner is formed in the burner insert wall.

Burner inserts for a gas turbine combustion chamber and gas turbine

A burner assembly for a firing system for firing fluidic fuels is provided. The burner assembly has a burner hub, an air inlet channel and a fuel inlet channel, wherein the fuel inlet channel is at least partially designed in the burner hub. A screening wall is arranged in the fuel inlet channel. The screening wall is spaced apart from a wall of the fuel inlet channel so that an intermediate space is formed between the wall of the fuel inlet channel and the screening wall. A sleeve is equipped with at least one radial positioning means that ensures a clearance of the sleeve from the wall of the fuel inlet channel. The at least one radial positioning means of the sleeve is designed as a positioning projection arranged in a circular manner, protruding out radially.

Shielding wall for a fuel supply duct in a turbine engine

Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel.

Fuel lance for A burner

A burner arrangement is provided. The burner arrangement includes a support and at least two fuel nozzles attached to the support in the direction of flow, with each fuel nozzle including a support-side section which includes a contact surface on the support side with which it rests on a supporting surface of the support, with at least two fuel nozzle tips embodied in one piece extending out from the support-side section in the direction of flow and the support-side contact surface including at least two extension parts projecting in the direction of the support, with the extension parts each embodying a channel through which fuel is fed in each case to the fuel nozzle tips through passages which are arranged in the support-side contact surface of the support-side section.

Burner arrangement

A burner for a gas turbine including a main burner and a pilot burner is provided. The main burner has a supporting structure, a heat shield and a holder for the heat shield, and wherein the holder is at least partially located within the supporting structure and the heat shield is at least partially located within the holder. The heat shield is fastened to the holder by a force-fit and/or a frictional connection.

Burner for a gas turbine

A method for producing a fuel nozzle is provided. In the method a swirl duct is mounted in an outer jacket surface of a pin and/or in an inner surface of a sleeve and the pin is attached in the sleeve so that the outer jacket surface of the pin is connected to the inner surface wherein the pin is disposed in the sleeve. The outer jacket surface of the pin and/or the inner surface of the sleeve includes at least one-swirl duct. A fuel nozzle and a burner are also further disclosed wherein the burner includes the fuel nozzle.

Fuel nozzle having swirl duct and method for producing a fuel nozzle

Growing community of inventors

Duisburg, Germany

Tobias Krieger