Siemens Aktiengesellschaft

Siemens Power Generation, Inc.

Siemens Energy Global Gmbh & Co. Kg

Marc Tertilt

Holger Grote

Andreas J Heilos

Wolfgang Kollenberg

Marco Link

Thorsten Engler

Manuel Gutermuth

Philipp Kreutzer

Markus Gorynski

Jay Alan Morrison

Gary Brian Merrill

Andreas Böttcher

Michael Anthony Burke

Werner Krebs

Daniel George Thompson

Oliver Schneider

Berthold Köstlin

Ulrich Wagner

Jens Kleinfeld

Matthias Hase

Olga Deiss

Christian Lerner

Nicolas Savilius

Bernd Vonnemann

Milan Schmahl

Kai Suselbeck

Margarete Herz

Christine Rasch

Thomas Grieb

Andre Kluge

Christian Beck

Marco Larson

Christine Taut

Björn Buchholz

Thomas-Dieter Tenrahm

Daniel Hofmann

Sabine Tüschen

Gerhard Simon

Bernd Stöcker

Uwe Gruschka

Oliver Lüsebrink

Stefan Reich

Wilhelm Scheidtmann

Karl Klein

Sabine Grendel

Marcus Fischer

Thomas Kerstiens

Stefan Hoffmann

Frank Weidner

Simon Bez

Matthias Kleinenhammann

Norbert Knüwer

Kai Süselbeck

Claudia Barbeln

Beate Seiler

Marvin Hümbs

Andreas Heilos

Kai SÜSELBECK

Andreas BÖTTCHER

Andre Botzen

Claudia Alders

A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%.

Partial-load operation of a gas turbine with an adjustable bypass flow channel

A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.

Method for operating a gas turbine below the nominal power thereof

A heat shield element for a heat shield has a support structure. The heat shield element includes a hot side which can be exposed to hot gas, a cold side opposite the hot side, and peripheral sides connecting the hot side to the cold side. The heat shield element can be fastened to the support structure of the heat shield with the cold side facing the support structure and has a height running vertically to the cold side. The height of the heat shield element increases in a rising direction, the rising portion of the heat shield element running in the rising direction substantially up to at least one peripheral side or up to a projection that extends the hot side over the base surface of the cold side.

Wedge-shaped ceramic heat shield of a gas turbine combustion chamber

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 gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.

Gas turbine and method for operating the gas turbine

There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot side to the cold side and a material volume which is defined by the hot side, the cold side and the peripheral sides, wherein the material volume comprises at least two material areas which are made of different materials. The materials are different from each other at least in respect of their resistance and/or thermal expansion coefficient.

Heat shield element, method and mold for the production thereof, hot-gas lining and combustion chamber

A highly durable, high-strength thermal shield element is provided for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal shield element comprises a base produced from a solidified cast ceramic material into which a plurality of reinforcing elements are integrated, to increase the tensile strength of the thermal shield element.

Heat shield element, in particular for lining a combustion chamber wall

A heat shield element arrangement including a heat shield element for a heat shield arranged on a supporting structure is provided. On each of the two opposing sides running parallel to the installation grooves the heat shield element includes a continuous screw head opening which penetrates the cold side and the hot side of the heat shield element substantially vertically and through which the screw head of the respective screw is arranged to be accessible to the supporting structure, and a spring element may be arranged under the respective screw, which spring element may be extended along the hot side of the heat shield element and the parallel installation groove of the supporting structure. An outer end of the spring element is embodied as a clamping retaining hook which is provided for the purpose of engaging in the laterally recessed retaining groove of the heat shield element.

Heat shield element arrangement and method for installing a heat shield element

Disclosed is a molding compound for producing a fireproof lining, especially for a combustion chamber of a stationary gas turbine. The molding compound is characterized particularly by the fact that the molding compound is formed from more than about 50 percent by weight of silicon carbide and less than about 50 percent by weight of aluminum silicate.

Molding compound for producing a fireproof lining

Disclosed is a molding compound for producing a fireproof lining, especially for a combustion chamber of a stationary gas turbine. Said molding compound is characterized particularly by the fact that the molding compound is formed from more than about 50 percent by weight of silicon carbide and less than about 50 percent by weight of aluminum silicate.

A retaining element for retaining a heat shield element on a support structure comprises at least one fixing section adapted to fix the retaining element to the support structure and at least one retaining section adapted to engage with an engaging groove present on a periphery of the heat shield element. A projection is arranged on the retaining element in such a manner that it projects in the direction of the heat shield element when retaining a heat shield element.

Retaining element and heat shield element for a heat shield and combustion chamber provided with a heat shield

A combustion chamber wall in a combustion chamber is proposed, The chamber wall has a support structure with a number of heat shield which are attached to the support structure with the aid of a fastening unit. The fastening unit encompasses a spring device which is fixedly connected to the support structure and is composed at least of a spring that is mounted in a jacket. The spring is secured against falling out on the side facing away from the combustion chamber by a first removable retainer. The interior of the spring device is provided with an axial hole for accommodating the fastening unit. The spring is secured against falling out on the side facing the combustion chamber by a second removable retainer. The spring device can be dismounted on the side facing the combustion chamber.

Combustion chamber wall

Thermal shield, especially for lining the wall of a combustion chamber

The invention relates to a heat shield block, particularly for lining a combustion chamber wall, with a hot side that can be subjected to the action of hot medium and with a wall side situated opposite the hot side. A core area, which has a core material, extends inside the heat shield block from the hot side to the wall side. The core area is surrounded by an edge area with an edge material whose heat conductivity is lower than that of the core material. This targeted thermal insulation in the edge area provided in the form of a material bond between the core material and the edge material renders the heat shield block particularly unsusceptible to the formation and growth of cracks in the core area on the hot side. The invention also relates to a combustion chamber provided with heat shield blocks of the aforementioned type, and to a gas turbine provided with a combustion chamber comprising such a heat shield block.

Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine

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Hattingen, Germany

Marc Tertilt