Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Michael Huth

Yevgeniy P Shteyman

James S Marshall

Matthias Hase

Robert Angel

Drew Ehlert

Peter Tiemann

Frank Hannemann

Bernd Prade

Andreas J Heilos

Clifford E Johnson

Tobias Buchal

Werner Krebs

Berthold Köstlin

Weidong Cai

Iris Oltmanns, Legal Representative

John Carl Glessner

Roland Liebe

Harald Nimptsch

Krishna C Miduturi

Udo Schmitz

Marcus Fischer

Sven Bethke

Stefan Dederichs

Yohannes Ghermay

Thomas Primke

Mark Seifarth

Ben Karanja

Anatol Schulz

Ramsatish Kaluri

Jens Prof Von Wolfersdorf

Thomas Pechette

Bernhard Prof Weigand

Diane Lauffer

Hans-Jürgen Kiesow

James Marshall

Andreas Heilos

Berthold Koestlin

A burner component of a burner. The burner has a flow channel, in which combustion air flows in a flow direction from upstream to downstream. The burner component includes a wall portion, which adjoins the flow channel; a plurality of injection nozzles, which are arranged in the wall portion; and a plurality of vortex generators, which are arranged on the wall portion. The vortex generators have a concavely curved sloped surface rising in the flow direction to improve the distribution of the fuel in the combustion air.

Burner component of a burner, and burner of a gas turbine having a burner component of this type

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 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 swirl generator, a method for preventing flashback in a burner with a swirl generator and a burner are provided. The swirl generator includes a central fuel distributor element, an outer wall enclosing the central fuel distributor element and bounding an axial flow channel for combustion air, swirl vanes extending in a radial direction to the outer wall and giving the flowing combustion air a tangential flow component, and a separating wall enclosing the central fuel distributor element and being positioned radially within the outer wall. The separating wall divides the flow channel into a radially inner channel segment and a radially outer channel segment. The radially inner channel segment allows the combustion air to pass without giving it a tangential flow component or while giving it a tangential flow component counter to the orientation of the tangential flow component in the radially outer channel segment.

Swirl generator, method for preventing flashback in a burner having at least one swirl generator and burner

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

The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of heat shield elements. The or each heat shield element, together with the combustion chamber wall, forms an interior space that can be subjected to the action of a coolant. The aim of the invention is to provide a combustion chamber with a comparatively simple design that has a high system efficiency. To this end, the invention provides that a flow element is placed in the respective interior space while serving to effect a locally specific control of the flow of coolant.

Combustion chamber

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

A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Combustion chamber for a gas turbine with at least two resonator devices

Growing community of inventors

Essen, Germany

Michael Huth