Alstom Technology Limited

General Electric Company

Ge Infrastructure Technology, LLC

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Piero-Daniele Grasso

Alexander Stankowski

Sophie Betty Claire Duval

Julien Rene Andre Zimmermann

Norbert Lucke

Sven Olliges

Sophie Duval

Johannes Clemens Schab

Thomas Baumann

Selim Akin

Yusuf Eren Ozturk

Jaroslaw Leszek Szwedowicz

Michael Seemann

Joergen Ferber

Fabrizio Mangano

Daniel Beckel

Thomas Widmer

Daniel Reitz

Fernando Manuel Santos Silverio

Marie-Gilles Barril

Mustafa Yuvalaklioglu

Simone Hoevel

Mauro Melas

Sabrina Puidokas

An automated system is provided. The system includes: a manipulator coupled to: an opening forming device configured to create an opening having a predefined geometry partially into a multilayer component at a selected location on a surface of the multilayer component, where the multilayer component includes a plurality of material layers including at least a substrate and a bond coat, and where the opening exposes each of the plurality of material layers; and an imaging device configured to create an image of the exposed plurality of material layers in the opening; and a processor configured to calculate at least a thickness of the bond coat of the exposed plurality of material layers from the image and based on the predefined geometry of the opening. Methods of using the system to analyze layer thickness of a multilayer component and repair a multilayer component are also provided.

Non-invasive quantitative multilayer assessment method and resulting multilayer component

A system for analyzing layer thickness of a multilayer component is provided. The system includes: an opening forming device configured to create an opening having a predefined geometry partially into the multilayer component at a selected location on a surface of the multilayer component, where the multilayer component includes a plurality of material layers including a substrate and a bond coat and the opening exposes each of the plurality of material layers, and an imaging device configured to create an image of the exposed plurality of material layers in the opening. The system is configured to calculate at least a thickness of the bond coat of the exposed plurality of material layers from the image and based on the predefined geometry of the opening. The system may also include a repairing device configured to repair the opening, allowing the multilayer component to be used for an intended purpose.

A method of analyzing layer thickness of a multilayer component is provided. The method includes: creating an opening having a predefined geometry partially into the multilayer component at a selected location on a surface of the multilayer component. The multilayer component includes a plurality of material layers including a substrate and a bond coat. The opening exposes each of the plurality of material layers including the substrate. Contrast of the exposed plurality of material layers can be increased. An image is created of the exposed layers in the opening using a digital microscope, and thickness of a bond coat, thickness of a depletion layer\ and/or thickness of an oxide layer is calculated from the image and based on the predefined geometry of the opening. Repairing the opening, allows the multilayer component to be used for an intended purpose after testing, e.g., re-installed and reused in a gas turbine.

Methods of repair of a component or adding material to a component using laser welding are disclosed. One method may include repairing or adding material to the component by laser irradiating a wire material with a laser in an inert gas in a vicinity of the component. The laser irradiating the wire material includes modulated pulsing the laser through: a warm up phase during which an on-power of the laser is increased over time to a maximum target on-power, a melt and bond phase during which the wire material is melted and during which the on-power is less than the maximum target on-power, and a stress releasing phase during which the on-power of the laser is less than the on-power during the melt and bond phase. The laser irradiated wire material forms a weld material to repair a damaged area or add material to the component.

Laser welding of component

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

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.

Comprehensive method for local application and local repair of thermal barrier coatings

A turbomachine blade () includes a blade body () and a corrosion and erosion protective multilayered coating () bonded thereto, the multilayered coating () including an erosion resistant first layer () at least covering a corrosion and erosion critical area () of the blade body () and a sacrificial second layer () provided over the first layer () at least covering the first layer (), preferably covering the blade totally. A method of manufacturing such a turbomachine blade includes the steps of providing a blade and depositing the erosion resistant first layer on the blade body so as to cover at least the corrosion and erosion critical area, followed by depositing the sacrificial second layer over the first layer at least covering the first layer.

Growing community of inventors

Niederweningen, Switzerland

Piero-Daniele Grasso