General Electric Company

Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Christoph Appel

Urs Benz

Stefan Rofka

Uwe Rüdel

Martin Schnieder

Ghislain Singla

Jörg Krückels

Richard Smith

Joerg Rinn

Ivan Lenuzzi

Ralf Jakoby

Samuel Fux

Andreas RÜTER

Rudolf Kellerer

Eric MÜLLER

Daniel Burri

Adrien Studerus

Alan Russel Jenney

Adam Wesniuk

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

Growing community of inventors

Umiken, Switzerland

Christoph Appel