Alstom Technology Limited

Rudolf Lachner

Adnan Eroglu

Martin Zajadatz

Thiemo Meeuwissen

Stanka Kokanovic

Susanne Renate Schell

Darrel Shayne Lilley

Falk Ruecker

Piotr Siewert

James Robertson

Rolf Anders Lindvall

A method is provided for switching over a gas turbine burner operation from liquid fuel to gas fuel and vice-versa, with the burner comprising nozzles for feeding a premixed gas fuel, nozzles for injecting a pilot gas fuel and nozzles for injecting a liquid fuel. According to the method, while the liquid fuel and the premix gas fuel are regulated to switch over from liquid fuel to gas fuel operation or vice-versa, the pilot gas fuel is controlled at a substantially constant flow rate.

Method for switching over a gas turbine burner operation from liquid to gas fuel and vice-versa

A combustion chamber is provided and includes a combustion device and a supply circuit arranged to feed fuel at a plurality of locations of the combustion device. The supply circuit includes manifolds collecting fuel to be distributed among at least some of the locations, ducts extending from the manifolds and feeding the locations. Some of the ducts carry valves having a plurality of predetermined working positions, each working position corresponding to a different fuel flow through the valve.

Combustion chamber and method for damping pulsations

A burner arrangement is disclosed with a conical swirler in the form of a double cone which is arranged concentric to a burner axis and which encloses a swirl chamber, and with a central fuel lance which lies in the burner axis and projects from the cone point of the swirler into the swirl chamber, wherein a first stage is provided for injecting premix fuel, in which the premix fuel is injected radially outwards into the swirl chamber through injection openings which are arranged on the fuel lance, and wherein a second stage is provided for injecting premix fuel, in which the premix fuel is injected into an air flow, which is guided in the double cone, through injection openings in the double cone. With such a burner arrangement, the gas pressure which is required in the first stage is reduced by the entire premix fuel being injected into the swirl chamber in the first stage through two oppositely-disposed injection openings with increased opening diameter.

Burner arrangement

A method for operating a gas turbine plant utilizing sequential combustion is provided. The gas turbine plant includes a compressor for compressing inducted combustion air, a first combustion chamber for combustion of a first fuel by utilizing the compressed combustion air, with a first turbine which is connected downstream of the first combustion chamber, and a second combustion chamber for combustion of a second fuel by utilizing the gases which emerge from the first turbine, with a second turbine which is connected downstream of the second combustion chamber. The method provides quick running up with simultaneously low emissions and homogeneous distribution of the turbine inlet temperature is achieved by the second combustion chamber being completely shut down for achieving a low partial load mode of the gas turbine plant.

Method for operating a gas turbine plant

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Attenkirchen, Germany

Rudolf Lachner