Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Jürgen Meisl

Andreas Böttcher

Timothy A Fox

Bernd Prade

Tobias Krieger

Werner Krebs

Kai-Uwe Schildmacher

Berthold Köstlin

Matthias Hase

Andre Kluge

Thomas Grieb

Christian Beck

Jaap Van Kampen

Eberhard Deuker

Patrick Ronald Flohr

Martin Lenze

Stefan Reich

James Smith

Siegfried Bode

Axel Mayr

Mariano Cano Wolff

Sabrina Isolde Siebelist

Christopher Grandt

Benjamin Witzel

Dennis Nehlsen

Sebastian Pfadler

Uwe Remlinger

Thomas Alexis Schneider

Paul Pixner

Bernhard Wegner

A pilot cone for use in a burner arrangement having a pilot burner includes a casing which widens downstream along a burner axis and has a plurality of cooling air passages passing through it; an inner wall which extends upstream starting from the upstream end of the casing; an annular gap which runs along the inner wall on the radially outer side; and a plurality of cooling air openings which establish a connection between the annular gap and the cooling air passages. Another wall extends upstream at a distance from the inner wall starting from the casing and delimits the annular gap on the radially outer side, the inner wall having a plurality of holes.

Pilot cone cooling

A gas turbine with a burner, which gas turbine has at least one fuel feed line and at least one fuel outflow line, wherein a flushing water line is connected fluidically to the fuel feed line, and wherein a leakage oil tank is connected fluidically via a drainage line to the fuel outflow line and the connection of the fuel outflow line and the drainage line is provided at a point downstream of at least one closure valve in the fuel outflow line, wherein a bypass line is connected fluidically to the fuel outflow line upstream of the closure valve, which bypass line connects the fuel outflow line fluidically to the leakage oil tank.

Gas turbine with a bypass line for improved fuel line flushing, and method for flushing a gas turbine

A method for running up a stationary gas turbine is provided. The turbine has a combustion chamber, the burners of which have a pilot burner and a main burner and by which various types of fuel are introduced into the combustion chamber for burning. The method, carried out while a rotor of the gas turbine is accelerating from a standstill to a nominal speed, includes feeding fuel of a first type of fuel to the pilot burners and feeding fuel of the first type of fuel to the main burners. In order to provide a method in which a comparatively low supply pressure is required in the fuel supply system and in which combustion vibrations that put the machine at risk are avoided during the running-up process, it is proposed that fuel of a second type of fuel is fed to the burner before the nominal speed is reached.

Method for running up a stationary gas turbine

A burner insert for a gas turbine combustion chamber is provided. The burner insert includes a burner insert wall including a cold side and a hot side, an edge delimiting the burner insert wall. The edge includes an edge bar extending at least partially circumferentially and projecting beyond the cold side. A burner opening for inserting a burner is formed in the burner insert wall.

Burner inserts for a gas turbine combustion chamber and gas turbine

Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel.

Fuel lance for A burner

Growing community of inventors

Mülheim an der Ruhr, Germany

Jürgen Meisl