Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Alen Markovic

Michael Thomas Maurer

Jost Imfeld

Remigi Tschuor

Jeffrey Alan De Jonge

Lothar Schneider

Hartmut Hähnle

Vedran Druzak

Giancarlo Ruggieri

Harmut Hähnle

Damir Cankovic

Stevica Furdek

Nikola Vranjic

Igor Bizic

Goran Mihelic

A burner assembly of a gas turbine comprising: a tubular body defining the flow path for the hot gas of the combustion during the turbine operation; an aperture for a fuel lance; a wearing ring of a sacrificial material configured to correspond to the edge of the aperture; a contacting leg extending from the wearing ring on the tubular body; a pre-tension system configured to contact the contacting leg in order to provide a pre-tension force on the ring.

Burner assembly for a burner of a gas turbine

In order to provide an annular combustion chamber () which can be heated without thermal distortion, expands without distortion, and is reliably closed, and for repairs can be opened and permanently closed again and can be reconditioned, the inner and/or outer shell () of an annular combustion chamber () is produced from a rotationally symmetrical sheet metal. For assembly, the shells are cut open along a split line (), and the lower half of the inner and of the outer shell () is introduced into the lower casing half of a gas turbine. After the insertion of the rotor, the two upper shell halves can likewise be inserted and be connected to the lower halves by welding. In order to improve the service life of the split line weld seam (), film cooling of the weld seam is routed by an indentation. This may be implemented, for example, by welded-in split line elements () which are also suitable for retrofitting.

Gas turbine with welded combustor liners

Growing community of inventors

Karlovac, Croatia

Alen Markovic