Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Claus Krusch

Andreas Böttcher

Werner Stamm

Bernd Prade

Marc Tertilt

Matthias Gralki

Daniel Schmidt

Holger Grote

Andre Kluge

Christos Georgios Aneziris

Nora Gerlach

Tobias Krieger

Volker Vosberg

Jens Kleinfeld

Matthias Hase

Patrick Lapp

Brigitte Heinecke

Elmar Pfeiffer

Daniel Vogtmann

Thomas-Dieter Tenrahm

Sabine Tüschen

Hartwig Dümler

Christopher Grandt

Sabine Grendel

Kai-Uwe Schildmacher

Raoul Galic

Margarete Neuhaus

Peter Danyluk

Marvin Hümbs

Hartwig DÜMLER

Andreas BÖTTCHER

Ulrich WÖRZ

A ceramic resonator for combustion chamber systems and combustion chamber system, wherein the resonator is annular when seen in the axial throughflow direction and has cavities in the interior, the cavities having at least one resonator neck per cavity as a connection to the inner surface of the ceramic resonator. By using a ceramic resonator, the amount of cooling air required is significantly reduced.

Ceramic resonator for combustion chamber systems and combustion chamber system

An annular resonator with a multiplicity of perforations for installation into a combustor arrangement of a static gas turbine installation, wherein the resonator is produced from refractory ceramic. A combustor arrangement for a gas turbine installation with a combustor unit, has a combustor, with a transfer line, which is arranged downstream of the combustor unit and which is designed to conduct hot gas generated by the combustor to a turbine, and with at least one resonator.

Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonator

A tubular combustion chamber system for a gas turbine unit includes a plurality of annularly arranged transition lines, which are designed to be connected at the upstream ends thereof to respective burners and to conduct hot gas produced by the burners to a turbine. The tubular combustion chamber system has a hot gas distributor, which is designed to be connected to the turbine and defines a ring channel, which is open to the turbine and into which the downstream ends of the transition lines lead. A gas turbine unit includes a plurality of annularly arranged burners, a turbine and a tubular combustion chamber system which connects the burners to the turbine.

Tubular combustion chamber system and gas turbine unit having a tubular combustion chamber system of this type

A combustion chamber, in particular for a gas turbine, includes a support structure, a plurality of retaining elements fastened to the support structure, and a plurality of heat shield elements which jointly form a heat shield and which each have a hot gas side, a cold gas side and end faces which interconnect the hot gas side and the cold gas side, the retaining elements interlockingly engaging in recesses in the heat shield elements. The retaining elements each have at least two engagement portions for interlockingly engaging in the recesses in a heat shield element, which engagement portions are interconnected in a tensionally rigid manner and are tensionally rigid themselves. Spring elements extend between the support structure and the heat shield elements, which spring elements are designed in particular as leaf springs and effect a frictional connection between the engagement portions of the retaining elements and the heat shield elements.

Combustion chamber

A seal for sealing a gap in a combustion arrangement of a gas turbine. The seal is formed by a L-shaped angle profile and a clamping profile. Both profiles have on the opposite side an engagement flank for fastening in a sealing groove and a sealing flank bearing against one another. The clamping profile further includes a holding portion, which is located opposite the associated sealing flank and also bears against the sealing flank of the angle profile, and a clamping portion connecting the sealing flank to the holding portion.

High-temperature seal having a clamping profile

A heat shield with support structure and a number of heat shield blocks secured thereto, having a cold side facing the support structure and a hot side opposite the cold side. At least one recess is arranged in at least one heat shield block circumferential face, connecting the cold to hot side. An opening connecting the recess to the cold side runs in the circumferential face perpendicularly to the cold side. A securing bolt inserted into the opening secures the heat shield block to the support structure. A bolt head protrudes at least partly into the recess. The securing bolt passes through an angled plate having first limb extending substantially parallel to the circumferential face and second limb extending into the recess. The angled plate has a reinforcing device extending beyond the pure angular shape to increase a resistance of the angled plate against bending due to the securing bolt.

Securing a heat shield block to a support structure, and heat shield

A material composition for producing a fireproof material having a fine-grain fraction with grain sizes of less than 100 &#x3bc;m and a coarse-grain fraction with grain sizes of more than 100 &#x3bc;m is provided. The fine-grain fraction includes aluminum oxide having a weight proportion of at least 90% by wt. in relation to the total weight of the fine-grain fraction, zirconium oxide having a weight proportion of up to 5% by wt. in relation to the total weight of the fine-grain fraction, a stabilizer for the zirconium oxide as well as titanium oxide powder having a weight proportion of up to 5% by wt. in relation to the total weight of the fine-grain fractional. The coarse-grain fraction represents a weight fraction of more than 30% by wt. of the material composition.

Material composition for producing a fireproof material and the use thereof, and fireproof molded body and method for the production thereof

A method for producing a refractory molded boy using a material composition having a fine-grain fraction with grain sizes of less than 100 &#x3bc;m and a coarse-grain fraction with grain sizes of more than 100 &#x3bc;m. The method includes the steps of adding a dispersing agent and/or a liquefier to the material composition unless the material compositing already includes the dispersing agent and/or liquefier, forming the material composition into a molded body, and sintering the molded body at a temperature above 1300 degrees Celsius.

A gas turbine burner with an igniter and an ignition electrode for installation in a main burner of a gas turbine is disclosed. The ignition electrode is protected from damage by a protective element.

Burner having a protective element for ignition electrodes

A method for repairing wider gaps in a substrate of a component by brazing at a brazing temperature is provided. Filler material and solder are prevented from separating in that, in a two-stage process, first the filler material and then the solder are applied to the wider gap. The powder does not melt at the brazing temperature and the filler metal does melt at the brazing temperature.

Process for brazing wide gaps

In a combustion chamber wall for a combustion chamber having a combustion chamber outlet through which a hot combustion exhaust gas can exit the combustion chamber, the combustion chamber wall comprises an outlet end which surrounds the combustion chamber outlet, and the outlet end is provided with a tempering device.

Combustion chamber wall, gas turbine installation and process for starting or shutting down a gas turbine installation

Growing community of inventors

Mülheim an der Ruhr, Germany

Claus Krusch