Alstom Technology Limited

General Electric Company

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Uwe Rüdel

Urs Benz

Christoph Appel

Adnan Eroglu

Ewald Freitag

Martin Schnieder

Remigi Tschuor

Andreas Huber

Jörg Krückels

Hartmut Hähnle

Ivan Lenuzzi

The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone. Local spacer ribs are provided at the leading edge of the liner segments in order to establish a gap of minimum width between the liner segments and the fixing segments of the neighboring first zone.

Annular combustion chamber of a gas turbine and gas turbine with such a combustion chamber

A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.

Transitional region for a combustion chamber of a gas turbine

An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat.

Gas turbine combustor including an acoustic damper device

A thermal machine, especially a gas turbine, includes an annular combustor which is outwardly delimited by an outer shell and an inner shell () and through which a hot gas axially flows. The outer shell and inner shell () are each provided with a concentric cooling shroud () which is attached at a distance on their outer side, forming a cooling passage () through which cooling passage () cooling air flows in a direction which is opposite to the hot gas flow. The cooling of the combustor is improved by at least one of the cooling shrouds (), on the side on which the cooling air enters the cooling passage (), having an outwardly curved, rounded inlet edge () for improving the inflow conditions.

Thermal machine

Growing community of inventors

Baden-Rütihof, Switzerland

Uwe Rüdel