Alstom Technology Limited

Sophie Duval

Alexander Stankowski

Piero-Daniele Grasso

Sven Olliges

Joergen Ferber

Daniel Reitz

Fernando Manuel Santos Silverio

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

A method for the application and/or renewal of a protection for a thermal barrier coating system of a heat engine involves a thermal barrier coating system that includes a bond coat layer () and a thermal barrier coating layer () of porous structure (), wherein the bond coat layer () is located between and in contact with a base metal () of a heat engine component and with the thermal barrier coating layer () and bonds the thermal barrier coating layer () to the base metal (). At least one substance is applied inside the engine as a liquid or carried by a liquid by spraying and/or by flowing it across a hot gas exposed surface () of the barrier coating layer () of the heat engine component mounted within the heat engine in the assembled state prior to the initial start-up of the engine, before the first operation interval, or during a washing cycle of the thermal engine and/or at the end of an operation interval, before a subsequent operation interval, wherein the substance covers and/or at least partly penetrates into the porous structure (), and concomitantly or subsequently hardens to remain within the pores () and/or on the upper surface () of the thermal barrier coating layer. Preferably, but not necessarily, for the application, the turbine washing equipment of the engine is used.

Methods for the protection of a thermal barrier coating system and methods for the renewal of such a protection

A method for the local initial application of a thermal barrier coating layer (), or for the local repair of coating defects and/or deteriorations of components () in the hot gas path of a gas turbine engine, which components are coated with a thermal barrier coating layer, includes at least the following steps: Steps (IV)a, (V) and (VI) can be omitted with the provision that at least one of steps (IV)a or (VI) is carried out.

Growing community of inventors

Zurich, Switzerland

Sophie Duval