Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Werner Krebs

Bernd Prade

Matthias Hase

Thomas Grieb

Peter Kaufmann

Andreas Böttcher

Anthony L Schiavo

Marc Tertilt

Tobias Krieger

Clifford E Johnson

Jan Wilkes

Berthold Köstlin

Weidong Cai

Olga Deiss

Michael Huth

Patrick Lapp

Christian Beck

Ulrich Wörz

Jaap Van Kampen

Eberhard Deuker

Malte Blomeyer

Andreas Bauer

Björn Buchholz

Jürgen Meisl

Peter-Andreas Schneider

Patrick Ronald Flohr

Daniel Vogtmann

Danning You

Martin Stapper

Peter Berenbrink

Krishna C Miduturi

Holger Streb

Stefan Reich

Dieter Simon

Udo Schmitz

Berthold Sturm

Martin Lenze

Patrick Flohr

Martin Müller

John M Crane

Lennard Helmers

Joachim Lepers

Andreas Diebels

Mark F Rubio

Thomas Hesse

Simon Bez

Günther Schulze

Yohannes Ghermay

Thomas Primke

Mark Seifarth

Ben Karanja

Dieter Warnack

Heinrich Thölking

Stefan Pernau

Siegfried Bode

Thomas Hahner

Sebastian Pfadler

Bernhard Wegner

David Barkowski

Martin Mueller

Heinrich Thoelking

A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

Method of selective combustor control for reduced emissions

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 combustion chamber for a gas turbine is provided. The combustion chamber comprises at least one first and one second jet carrier, of which at least one is provided for injecting an operating gas in the combustion chamber such that waste gas formed in the flame zone thereof is circulated to a mixing zone of the first jet carrier. In order to achieve a compact combustion chamber, the jet carriers are positioned in relation to each other such that waste gas from the flame zone of the first jet carrier flows directly to the mixing zone of the second jet carrier.

Combustion chamber for a gas turbine

The present disclosure provides a gas turbine combustor including a combustion structure () having a combustor liner () and a flow sleeve (). The combustor liner () includes inner and outer surfaces () and defines a combustion zone (). The gas turbine combustor further includes a plurality of hollow airfoil-shaped structures () affixed to the combustor liner () and extending radially outwardly into an airflow space () defined radially between the flow sleeve () and the combustor liner (). Each hollow structure () includes at least one metering tube () providing acoustic communication between the combustion zone () and the hollow structure (). The metering tubes () are detachably coupled to the combustor liner () for permitting interchanging of the metering tube () with at least one additional metering tube having at least one different dimension to effect a change in an acoustic characteristic of the hollow structure ().

Resonators with interchangeable metering tubes for gas turbine engines

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 regulating device for regulating the course of a gas turbine plant has at least one sensor for sensing a measurement variable and for outputting a measurement signal which represents the measurement variable; at least one adjusting system for influencing air and/or fuel supply to a combustion chamber of the gas turbine plant on the basis of a correcting variable; and a regulator connected to the at least one sensor so as to receive the measurement variable and to the at least one adjusting system for outputting the correcting variable, the regulator being designed to determine the correcting variable on the basis of the measurement variable received and its deviation from a pilot variable. At least one sensor is designed to sense the variation in time of at least one burner or combustion chamber parameter as measurement variable.

Method and device for regulating the operating line of a gas turbine combustion chamber

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 gas turbo set including a first turbine, a second turbine, and a combustion chamber connected between the first and second turbines and operated by auto-ignition is provided. The turbines and the combustion chamber are located on a common shaft that may be rotated about an axis. To increase the efficiency of the gas turbo set, the outer periphery of the second turbine is at a greater distance from the axis than that of the first turbine, leading to a reduction in the size and/or the number of turbine blades.

Gas turbo set and method for controlling a gas turbo set

Burners in prior art exhibit combustion instabilities in certain ranges. The operating range of burners is restricted by said instabilities. In an inventive burner, the combustible has a concentration distribution, whereby the concentration of the combustible reduces in a radial direction from the interior to the exterior.

Burner

This invention relates to a burner, especially a gas turbine burner, wherein a Helmholtz resonator downstream of a fuel inlet position in directly linked with a burner channel. In this manner, combustion oscillations do not arrive at the fuel inlet position, thereby reducing acoustic disturbances and air ration deviations which are the main cause for the formation of combined oscillations. The invention also relates to a method for operating a burner and a gas turbine.

Burner, method for operating a burner and gas turbine

The invention relates to a gas turbine comprising a combustor that extends into a combustion chamber. The port of the combustor is surrounded in a ring-shaped manner by a Helmholtz resonator, whereby combustion oscillations are effectively suppressed due to close contact with the flame while irregularities in temperature are prevented.

Gas turbine

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Mülheim an der Ruhr, Germany

Werner Krebs