Siemens Aktiengesellschaft

Olga Deiss

Andreas Böttcher

Bernd Prade

Marc Tertilt

Christoph Lehmann

Holger Grote

Tobias Krieger

Werner Krebs

Juan Enrique Portillo Bilbao

Jan Wilkes

Berthold Köstlin

Matthias Hase

Olaf Rehme

Jens Kleinfeld

Christian Scholz

Thomas Grieb

Andre Kluge

Christian Beck

Jaap Van Kampen

Patrick Lapp

Francois Benkler

Nicolas Savilius

Bernd Vonnemann

Rajesh Rajaram

Daniel Vogtmann

Marco Link

Patrick Ronald Flohr

Simon Purschke

Thomas Hauser

Günther Walz

Rostislav Teteruk

Christopher Grandt

Sabine Grendel

Stefan Dederichs

Bernd Reinarz

Anna Knödler

Marcus Zurhorst

Matthias Chlebowski

Claudia Barbeln

Fabian Sander

Julian Timmermann

Ljiljana Hanf

Sebastian Pfadler

Thomas Brandenburg

Bernhard Wegner

Andreas Heilos

Meike Jaspers

Alexander Mattes

Claudia Alders

A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (), and a plurality of mains () disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.

Combustor and method for damping vibrational modes under high-frequency combustion dynamics

A burner arrangement having a combustion chamber, a multiplicity of mixing ducts discharging into the combustion chamber, in which ducts combustion air and fuel introduced during proper operation are mixed, and at least one resonator which has a defined resonator volume and resonator openings. The mixing ducts have mixing tubes which extend axially through an annular space defined between a tubular outer wall, a tubular inner wall arranged with the radial separation from the outer wall, an annular end plate arranged upstream and an annular end plate arranged downstream, wherein the end plates are provided with through openings which receive and/or prolong the mixing tubes. The resonator openings of the at least one resonator are designed as air ducts that extend through the downstream end plate, and the resonator volume of the at least one resonator is formed by at least one part of the annular space.

Burner arrangement with resonator

A method for producing a component by selective laser melting, wherein a number of lasers arranged next to one another generate a laser field, as a result of which powdery material can be melted in a selective manner for the purposes of generating contours. In the process, individual lasers of the laser arrangement can be switched on or off in a selective matter in order to irradiate or not irradiate certain regions. Furthermore, a device for carrying out the method is provided.

Production of a component by selective laser melting

A burner assembly with a combustion chamber, a plurality of mixing ducts leading into the combustion chamber, where combustion air and introduced fuel are mixed. The mixing ducts are formed by mixing tubes extending axially through an annular space between a tubular outer wall, a tubular inner wall arranged radially at a distance from the outer wall, a ring-shaped end plate arranged upstream and a ring-shaped end plate arranged downstream. The end plates have through-openings, which accommodate and/or extend the mixing tubes, and the end plates have, both radially inside and outside, a circumferential edge extending in the direction of the annular space, with axial bores in the edge of the ring-shaped end plate arranged downstream. The axial bores extend from the annual space into the end plate, and at least one opening is for removing cooling air, the opening branching from the axial bore.

Bruner assembly

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

An adaptation method for a modelling method in which, by means of target geometry, model geometry, which is derived from the target geometry, is created for an object to be produced by a selective laser melting method is provided. In the adaptation method, adapted model geometry is produced from the derived model geometry by dimension adaptation by means of a correction factor and/or by geometry adaptation by means of correction geometry.

Adaptation method and production method for components produced by SLM

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 gas turbine combustion chamber is provided. The gas turbine includes a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross-section, wherein on the side of the combustion chamber wall facing away from the combustion chamber interior there is arranged over the entire cross-sectional circumference of the combustion chamber wall a corrugated component which, in combination with the combustion chamber wall, embodies a plurality of separate resonance chambers and wherein openings are incorporated in the combustion chamber wall in such a way that a fluidic connection is established in each case between the combustion chamber interior and one of the resonance chambers and wherein the corrugated component has two locking rings which are connected to the combustion chamber wall in order to seal off the resonance chambers.

Gas turbine combustion chamber

A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

Heat shield

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Düsseldorf, Germany

Olga Deiss