Alstom Technology Limited

Thomas Kueenzi

Marcel Stalder

Jonas Hurter

Hans Peter Knoepfel

Ian William Boston

Dieter Rebhan

Stefan Gross

A combustion chamber for an industrial gas turbine has thermal protective elements which are installed along the inner circumference of its casing. The thermal protective elements are cooled by cooling air which is added to the fuel in the region in front of a front casing section after the cooling. A brush seal is installed between the front casing section and the thermal protective elements, where the brush seal is configured in segments. The combustion chamber can be sealed against leakages of cooling air in all operating states of the combustion chamber.

Combustion chamber for a gas turbine

A method for running up a gas turbine plant ( ) is disclosed. In the method, a fuel ( ) is injected into the combustion chamber ( ) via a plurality of pilot burners ( ) and premix burners ( ). During the start-up and in a lower load range, the combustion chamber ( ) is operated in the pilot mode, and, at a specific time point, the combustion chamber ( ) is changed over from the pilot mode to the premix mode. The changeover time point from the pilot mode to the premix mode depends on a variable changeover temperature (T ), and this changeover temperature (T ) is determined from pulsations occurring in the flame of the combustion chamber ( ).

Method for running up a gas turbine plant

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Birsfelden, Switzerland

Thomas Kueenzi