Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Berthold Köstlin

Frank Hannemann

Andreas Böttcher

William Richard Ryan

Andreas J Heilos

Bernd Prade

Gerhard Zimmermann

Marc Tertilt

Jan Wilkes

Richard L Thackway

Olga Deiss

Christian Beck

Werner Krebs

Matthias Hase

Michael Huth

Thomas Grieb

Eberhard Deuker

Jaap Van Kampen

Daniel Vogtmann

Björn Buchholz

Jürgen Meisl

Martin Stapper

Rainer Nies

Stefan Reich

Martin Lenze

Stefan Dederichs

Kai-Uwe Schildmacher

Boris Ferdinand Kock

Simon Bez

Dennis Nehlsen

Boris Ferdinand Koch

Andreas Heilos

David Barkowski

Ulrich WÖRZ

Lars Terjung

A burner having a plurality of pre-mixing chambers each having a fuel nozzle for two fuels, the fuel nozzle has a fuel lance extending in a flow direction, in which fuel lance first outlet openings for a first fuel are introduced. The fuel lance is surrounded by an outer pipe having at least one second outlet opening for a second fuel, the first outlet openings oriented radially and the second outlet opening oriented axially, a flow cross-section is formed between the fuel lance and the inside of the pre-mixing chamber and vortex generators are arranged on the fuel lance. At least one vortex generator is arranged upstream of the first outlet openings and downstream of the second outlet opening. The distance of the first outlet openings from an end of the pre-mixing chamber is at least three times as large as a cross-section of the pre-mixing chamber.

Burner, gas turbine having such a burner, and fuel nozzle

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 method for running up a stationary gas turbine is provided. The turbine has a combustion chamber, the burners of which have a pilot burner and a main burner and by which various types of fuel are introduced into the combustion chamber for burning. The method, carried out while a rotor of the gas turbine is accelerating from a standstill to a nominal speed, includes feeding fuel of a first type of fuel to the pilot burners and feeding fuel of the first type of fuel to the main burners. In order to provide a method in which a comparatively low supply pressure is required in the fuel supply system and in which combustion vibrations that put the machine at risk are avoided during the running-up process, it is proposed that fuel of a second type of fuel is fed to the burner before the nominal speed is reached.

Method for running up a stationary gas turbine

A fuel nozzle () for two fuels, with an inner pipe () with radially oriented outlet openings () for a first fuel and with an outer pipe (), surrounding the inner pipe (), with axially oriented outlet openings () for a second fuel; an axially extending groove () on an outer surface of the inner pipe () and a projection () inward from the outer pipe which engages in the groove () as an anti-torsion device () and which is arranged between two axial outlet openings (). Alternative groove and projection configurations are disclosed.

Fuel nozzle having an inner tube and an outer tube engaged with the inner tube

A method for starting a burner for combusting synthesis gases is provided. The burner includes first and second fuel passages, the first fuel passage encompasses the second fuel passage in a substantially concentric manner and the gas transferred to the burner is mixed with combusting air and is combusted. In order to start the burner, the second fuel passage is first loaded with a synthesis gas to a predefined burner power at a first starting phase and the first fuel passage is loaded with the synthesis gas at a second starting phase.

Method for starting a burner

A turbine burner is provided. The turbine burner has a secondary feed unit and a primary feed unit. The primary feed unit has a primary mixing tube and a fuel nozzle that are arranged concentrically around the secondary feed unit. The primary mixing tube and the fuel nozzle have a fluid flow connection. The fuel nozzle has an annular wall that is radially spaced in the axial direction from the secondary feed unit such that a gap height is fainted by the annular wall and the secondary feed unit. The annular wall has an inside wall directed toward the secondary feed unit and having blades with a leading edge on the upstream side. The fuel nozzle has an inlet and the blades have an axial distance from the inlet. The ratio of the distance to the gap height is greater than 1 and less than the gap height.

Turbine burner having premixing nozzle with a swirler

A device for increasing service life of a combustion installation is disclosed. The combustion installation has a gas-conducting component and a conducted gas has dirt particles. The gas-conducting component has a layer which is partially detached together with the dirt particles of the gas when the layer is impinged with the gas and when a dirt particle is deposited on the layer.

Device and method for extending the service life of firing installations

The invention relates to a method for starting a burner for combusting synthesis gases, wherein said burner comprises first and second fuel passages, the first fuel passage encompasses the second fuel passage in a substantially concentric manner and the gas transferred to the burner is mixed with combusting air and is combusted. According to said invention, in order to start the burner, the second fuel passage is first loaded with a synthesis gas to a predefined burner power at a first starting phase and the first fuel passage is loaded with the synthesis gas at a second starting phase.

A method is for operating a burner of a gas turbine. A fossil fuel is gasified and the gasified fossil fuel is fed as synthesis gas into the burner for combustion. The burner is connected to the gas turbine. The synthesis gas is divided into a first partial current and a second partial current and the partial currents are each fed into the burner for combustion. A power plant, particularly a gas and steam turbine system, includes a gasification device for a fossil fuel.

Method for operating a burner of a gas turbine and a power plant

The invention relates to a pre-mix burner for burning a low-calorie combustion gas, said burner comprising an air duct which extends along an axis of the burner and can be used to supply combustion air. A swirling device is arranged in the air duct and is used to apply a swirling motion to the combustion air. An injection device for the low-calorie combustion gas is provided downstream of the swirling device. The injection device comprises inlets for the combustion gas, such that the formation of wake regions in the air channel is prevented. The invention also relates to a method for burning a low-calorie combustion gas, according to which a swirling motion is applied to the combustion air, low-calorie combustion gas is injected into the swirled combustion air and intensively mixed therewith, and the mixture is then burned.

Premix burner and method for burning a low-calorie combustion gas

Growing community of inventors

Duisburg, Germany

Berthold Köstlin