Alstom Technology Limited

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Alexander Stankowski

Piero-Daniele Grasso

John Fernihough

Andreas Boegli

Sven Olliges

Simone Hövel

Sophie Duval

Sophie Betty Claire Duval

Julien Rene Andre Zimmermann

Lukas Rickenbacher

Daniel Beckel

Frigyes Szuecs

Matthias Hoebel

Thomas Baumann

Thomas Etter

Alexander Schnell

Hartmut Haehnle

Jaroslaw Leszek Szwedowicz

Ulrich Wellenkamp

Günter Ambrosy

Roman Engeli

Hans Bissig

Joergen Ferber

Thomas Duda

Frigyes Szücs

Thomas Widmer

Hartmut Hähnle

Stefan Werner Kiliani

Rainer Kurtz

Marie-Gilles Barril

Ansgar Luttermann

Karsten Bindernagel

Simone Hoevel

Mauro Melas

Daniel Reitz

Fernando Manuel Santos Silverio

Sabrina Puidokas

Michal Tomasz Prugarewicz

Lukas Emanuel Rickenbacher

Grasso Piero-Daniele

Johannes Clemens Schab

Stefan Kiliani

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

In a method for manufacturing an article (), particularly a prototype of a product or component, a tool prototype or spare part, by using selected laser melting, for the application onto the article () of a layer () or portion of a second metallic material, which is different from the material of the first metallic powder (), a tape (), sheet (), foil or three-dimensional pre-form () of a second material is applied to the article () and is heated by a focused laser or electron beam () to a specified temperature such that the tape (), sheet (), foil or pre-form, respectively, are made molten by the electron laser beam (), wherein the focused beam () is applied to a given area corresponding to a selected cross-sectional area of the model of the article () under formation of a new layer or part made of second material integral with the article ().

Method of applying multiple materials with selective laser melting on a 3D article

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

A device for cleaning oxidized or corroded components (), especially gas turbine components which are exposed to hot gases, in the presence of a halogenous gas, includes a cleaning retort which is designed in the shape of a boiler or cylinder and into which, indirectly or directly, leads a feed line which is connected via a flow control unit to a gas reservoir which stores the halogenous gas, and in which a device for gas distribution is integrated. The flow control unit has a gas volume control valve (), a heat exchanger unit (), and also a gas volume measuring unit () in sequence along the throughflow direction of the halogenous gas which flows through the feed line. Furthermore, a gas distribution in the retort directs the halogenous gas directly to the components which are to be cleaned.

Device for cleaning oxidized or corroded components in the presence of a halogenous gas mixture

In a Ni-based, Co-based, or Ni&#x2014;Co-based braze alloy () for high-temperature brazing of components () of modular structure and for repairing damaged components () which are formed of single crystal or directionally solidified superalloys using said braze alloy (), the braze alloy has a first metallic powder component () having particle sizes in the nanometer range and a second metallic powder component () having particle sizes in the micrometer range. The surface of the particles of the second powder component () is thinly coated with particles of the first powder component (). The braze alloy () additionally includes grain boundary stabilizing elements as alloying elements. In addition, melting point depressants can be present in the braze alloy () in a commercially common quantity or with a considerably increased proportion. Both the melting temperature of the braze alloy () and the probability of recrystallization are advantageously reduced.

Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy

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 process produces a 3-dimensional component () by selective laser melting (SLM), in which the component () is formed on a foundation with a surface, e.g., a platform () or a support, which in particular is a component of the same type which has already been produced previously, by successively melting layers of a first metal powder to form a sequence of stacked layers. The process is substantially simplified and made more flexible by virtue of the fact that the separation of the finished component () from the surface of the platform () or the support thereof is simplified by providing a separating layer () between the component () and the platform () or the support, this separating layer making it possible to separate the finished component () from the platform () or the support without damaging the finished component ().

Process for producing a 3-dimensional component by selective laser melting (SLM)

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 process for extending the cyclic service life of thermal barrier coatings made of yttrium-stabilized zirconium oxide (YSZ) or the like which have been applied to a substrate with an oxidizing bond coat in between includes increasing or long-term stabilizing the strain tolerance of the thermal barrier coating.

Process for extending the cyclic service life of thermal barrier coatings, in particular on gas turbine components

An amorphous braze foil () produced by a melt-spin process has an upper side and a lower side. The upper side and the lower side are thinly coated with a film of metallic Ni-based, Co-based, or Ni&#x2014;Co-based braze powder () with a particle size in the nanometer range, wherein both the braze foil () and also the braze powder () additionally include grain boundary stabilizing elements as alloying elements. In addition, melting point depressants can be present in the braze foil or in the nano braze powder () in a commercially common quantity or with a considerably increased proportion. With the braze foil () coated in this manner, both the melting temperature of the braze material and also the probability of recrystallization are advantageously reduced when brazing in the adjacent base material ().

Braze foil for high-temperature brazing and methods for repairing or producing components using a braze foil

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 gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.

Gas turbine hot gas component repair method

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.

Turbomachine blade with erosion and corrosion protective coating and method of manufacturing

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Würenlingen, Switzerland

Alexander Stankowski