Siemens Aktiengesellschaft

Viessmann Holding International Gmbh

Marco Link

Andreas Böttcher

Markus Hofmann

Marc Tertilt

Andreas Heselhaus

Jan Wilkes

Nicolas Savilius

Thorsten Engler

Oliver Schneider

Olga Deiss

Thomas Grieb

Andre Kluge

Francois Benkler

Ulrich Waltke

Michael Wagner

Daniel Vogtmann

Philipp Kreutzer

Manuel Gutermuth

Markus Gorynski

Uwe Sieber

Thomas-Dieter Tenrahm

Sabine Tüschen

Patrick Bullinger

Gerhard Simon

Oliver Lüsebrink

Martin Lenze

Torsten Matthias

Ansgar Sternemann

Kai Suselbeck

Daniel Gloss

Stephan Klumpp

Wilhelm Scheidtmann

Carsten Kaufmann

Stefan Braun

Stefan Völker

Marc Mittelbach

Sabine Grendel

Karl Klein

Hubertus Michael Wigger

Thomas Klemke

Marcel Eifel

Richard Graefe

Manfred Hartmann

Rafael Labisch

Tjark Eisfeld

Kai Süselbeck

Christoph Buse

Elke Henschel

Eugen Gleim

Thomas Brandenburg

Horst Saathoff

Marion Morthorst

Michael Rollmann

Dirk MÜLLER

Kai SÜSELBECK

Meike Jaspers

Andreas BÖTTCHER

Andre Botzen

Arsène Brice Kadji

Rafael Labish

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 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

An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.

Internally coolable component for a gas turbine with at least one cooling duct

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

A passage wall section of an annular flow passage of an axial turbomachine is provided. A guide ring has a first toothing arrangement which is in contact with a second toothing arrangement arranged on a sidewall of a circumferential groove which accommodates the guide ring, wherein for axial displacement of the displaceable guide ring, the guide ring is rotatable in a circumferential direction.

Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment

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Mulheim, Germany

Marco Link