Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Matthias Hase

Yevgeniy P Shteyman

Andreas Böttcher

Timothy A Fox

Werner Krebs

James S Marshall

Bernd Prade

Marc Tertilt

Tobias Krieger

Clifford E Johnson

Oliver Schneider

Jan Wilkes

Claus Krusch

Berthold Köstlin

Jens Kleinfeld

Olga Deiss

Michael Huth

Thomas Grieb

Robert Angel

Drew Ehlert

Robert H Bartley

Christian Beck

Adam J Weaver

Patrick Lapp

Andre Kluge

Paul A Sanders

Ulrich Wörz

Jaap Van Kampen

Nicolas Savilius

Thomas-Dieter Tenrahm

Jürgen Meisl

Rajesh Rajaram

Daniel Vogtmann

Patrick Ronald Flohr

Björn Buchholz

Miguel Bascones

Martin Stapper

Peter Kaufmann

Martin Lenze

Udo Schmitz

Stefan Reich

Kai-Uwe Schildmacher

Manish Kumar

Mark F Rubio

Joseph L Evins

Sabine Grendel

Simon Bez

Lashanda N Williams

Mariano Cano Wolff

Vaidyanathan Krishnan

Siegfried Bode

Axel Mayr

Christopher Grandt

Khamhou Sayavong

Sebastian Pfadler

David Barkowski

Uwe Remlinger

Sachin S Terdalkar Terdalkar

Thomas Alexis Schneider

James Marshall

Paul Pixner

Bernhard Wegner

A burner arrangement has a plurality of mixing channels which extend parallel to the main axis of the burner arrangement and are arranged in at least two concentric circles, in which mixing channels fuel and discharge air from the compressor are mixed during the operation of the burner arrangement. The mixing channels are grouped together into fuel stages so as to produce an irregular staging in the peripheral direction of the burner arrangement.

Burner arrangement having a peripheral staging concept

A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener () may be arranged to provide support to an outer edge () of an exit frame () in a transition duct (). Stiffener () may be configured to circumferentially extend between mutually opposed corners () of the exit frame of the transition duct. A brace () may be connected to a centrally-disposed section () and may extend to support respective end portions () of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Transition duct support and method to provide a tuned level of support stiffness

A jet burner has a hot-gas side, which faces toward a combustion chamber during operation, and a cold-gas side, which faces away from a combustion chamber, including a base plate on which there are arranged multiple jet nozzles, wherein the base plate has at least one cooling duct, wherein the at least one cooling duct issues into a burner stage which comprises a pilot burner arranged on the base plate.

Jet burner with cooling duct in the base plate

A gas turbine system () including a burner arrangement having a tubular combustion chamber (), a turbine () and a transition duct () connecting the combustion chamber () and the turbine (), wherein the transition duct () is provided with an axially extending cooling air channel (). The transition duct () includes a plurality of axially extending cooling air channels, and wherein each cooling air channel () is provided with one single inlet () opened to the outside of the transition duct () and with one single outlet () opened to the inside of the transition duct ().

Gas turbine system with a transition duct having axially extending cooling channels

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 of a gas turbine including a reaction chamber and a plurality of jet nozzles opening into the reaction chamber is provided. Fluid is injected through an outlet into the reaction chamber by the jet nozzles using of a fluid stream wherein the fluid is burned into hot gas in the reaction chamber. An annular gap is disposed about the fluid stream for at least one jet nozzle so that a part of the hot gas is drawn out of the reaction chamber and flows opposite the fluid flow direction into the annular gap and is mixed with the fluid stream within the jet nozzle. The ring gap is formed by means of an insert tube, and wherein the insert rube includes a thickening at the upstream end. A method for stabilizing the flame of such a burner of a gas turbine is also provided.

Stabilizing the flame of a burner

A method for operating a burner comprising a burner axis and at least one jet nozzle is provided. The nozzle or nozzles include a central axis, a jet nozzle outlet, a wall that runs in a radial direction starting from the central axis and that faces the burner axis and a volumetric fluid flow that includes a fuel and flows through the jet nozzle or nozzles to the jet nozzle outlet. An air film is formed at the jet nozzle outlet between the volumetric fluid flow including the fuel and the wall that faces the burner axis by means of air that is injected into the jet nozzle or nozzles along the wall that faces the burner axis.

Method for operating a burner and burner, in particular for a gas turbine

A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

Gas-turbine burner having inflow guide means

A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

Gas-turbine burner

Growing community of inventors

Mülheim, Germany

Matthias Hase