Ansaldo Energia IP UK Limited

Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Sven Olliges

Alexander Stankowski

Piero-Daniele Grasso

Sophie Betty Claire Duval

Thomas Baumann

Weiqun Geng

Julien Rene Andre Zimmermann

Joergen Ferber

Sophie Duval

Thomas Widmer

Mauro Melas

Simone Hoevel

Jeton Nivokazi

Benjamin-Timo Zoller

Uwe Haarnagel

Grasso Piero-Daniele

A method and a turbine part having a coating with a matrix layer that includes a high temperature resistant hydrophobic polysiloxane filler, wherein the coating has superior mechanical strength and temperature resistance.

Coatings for turbine parts

A method for reconditioning a hot gas path part of a gas turbine to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of the hot gas path part, resulting in a cutout at the hot gas path part; and manufacturing a coupon for insertion into the cutout to replace the removed area of the hot gas path part. The method further includes inserting the coupon into the cutout; and joining the hot gas path part with the coupon. The coupon is manufactured by a selective laser melting method resulting in a fine grain sized material with significantly improved low cycle fatigue lifetime. The hot gas path part is coated, at least in an area including the inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue and oxidation lifetime.

Method for reconditioning a hot gas path part of a gas turbine

The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Method for coating a component of a turbomachine and coated component for a turbomachine

An abradable coating system (-) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue () or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element () has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component () includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element () or a complete abradable coating system is attached to the component (), preferably by using a matrix, wherein for example only a center part () or a fraction of a center part () is replaced.

Abradable coating system

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Dübendorf, Switzerland

Sven Olliges