Snecma

Snecma Services

Universite De La Rochelle

Centre National De La Recherche Scientifique

Safran Aircraft Engines

Université Paul Sabatier (Toulouse III)

Onera

Praxair Surface Technologies Inc.

Justine Menuey

Frédéric Braillard

Jérôme Brossier

Sarah Hamadi

Michel Vardelle

Fernando Pedraza Diaz

Aurelien Tricoire

Pierre J Josso

John Foster

Marie-Pierre Bacos

Andre Hubert Louis Malie

Baptiste Bouchaud

Gilles Bonnet

Jean-Pierre Bonino

Florence Ansart

Andre Hubert Malie

Fabrice Crabos

Juliette Hugot

André Hubert Louis Malie

Annie Pasquet

Josseline Balmain

Elise Nogues

Frederic Braillard

Serge Naveos

Marie Pierre Bacos

Celine Viazzi

Didier Ribot

Justine Fenech

Yannick Cadoret

Pascal Etuve

Stephen Owens

Alan Taylor

Martin Chatterney

Jerome Brossier

Céline Viazzi

To protect a superalloy substrate from oxidation and hot corrosion, disclosed herein is coating made by a process that deposits successive layers on the substrate, a first layer of aluminium and of at least one element capable of being alloyed with sulphur, and a second layer of a material that isolates the at least one element capable of being alloyed with sulphur.

Coating for protection against oxidation and against hot corrosion on a superalloy substrate

A method for repairing a blade forming a cathode and having a surface to be coated defining a critical area, utilizing an anode, an electrolyte bath including insoluble particles, and a mounting on which the blade is mounted in a working position relative to a reference wall. The mounting is placed in the bath, and the particles and the metal of the anode are co-deposited to form the coating on the surface to be coated. The anode is typically placed facing the critical area and the mounting includes a mechanism for monitoring current lines to obtain a coating with a relatively constant, predetermined thickness for the critical area, that gradually falls to a value of substantially zero along edges of the coating.

Method and an assembly for electrolytically depositing a coating

The invention relates to a method of fabricating a thermal barrier comprising a ceramic coating layer covering at least a portion of the structure of a substrate, wherein the ceramic coating layer is deposited on the substrate solely by a cathodic electrodeposition process between at least one cathode () and at least one anode (), the substrate being formed of an electron-conducting material and constituting the cathode. In characteristic manner, the electrolyte () comprises at least one salt from the group comprising the salts of lanthanides, of yttrium, of zirconium, and of hafnium, such that the coating layer applied by the electrodeposition process includes at least one oxide from the group comprising the oxides of lanthanides, of yttrium, of zirconium, and of hafnium, and it also includes a step of heat treating the ceramic coating layer at a temperature lying in the range 400&#xb0; C. to 2000&#xb0; C. for a duration of at least 10 min.

Method of fabricating a thermal barrier

To protect a superalloy substrate from oxidation and hot corrosion, disclosed herein is a process that deposits successive layers on the substrate, a first layer of aluminum and of at least one element capable of being alloyed with sulphur, and a second layer of a material that isolates the at least one element capable of being alloyed with sulphur.

Process for depositing a coating for protection against oxidation and against hot corrosion on a superalloy substrate

A process and device in production of precise three-dimensional sinters of a shape substantially close to that of an original part, using flash sintering produced by spark plasma sintering (SPS) technology. A mold is produced in a die of an enclosure for SPS flash sintering, the mold being shaped as an impression of the original part. The following are deposited in successive layers in the mold: a layer based on a superalloy powder, a metallic protection layer, and a thermal barrier layer. In a sintering, pressurization is initiated and a pulsed current passes through, producing a rapid rise in temperature in accordance with a flash sintering cycle whose temperature, pressure, and duration are regulated, with at least one temperature plateau and one pressure plateau. The layer of superalloy forms, by diffusion, during the sintering, a bonding continuum of material with the part to be repaired.

Process for local repair of a damaged thermomechanical part and part thus produced, in particular a turbine part

The invention relates to a part comprising a substrate made of an electron-conducting material and a coating over at least a portion of the surface of the substrate, the coating comprising a ceramic coating layer. In characteristic manner, said coating layer is based on cerium oxides and said coating layer presents oxygen vacancies at a concentration greater than or equal to 1&#xd7;10/cm. The invention is applicable to parts for high temperature applications, in particular in the field of aviation.

Part comprising a substrate carrying a ceramic coating layer

The invention relates to a method for manufacturing a thermal barrier protection covering a superalloy metal substrate and comprising at least one metal sublayer () and a ceramic layer () based on zirconia stabilized with yttrium having a column structure defining pores. The following steps are applied: Application to the protection of aeronautical protection parts.

Method for manufacturing a thermal-barrier protection and multilayer coating suitable for forming a thermal barrier

A method for forming a protective coating containing aluminum and zirconium on the surface of a metal part. The part is put into contact with a cement made of aluminum alloy, at a treatment temperature, with an atmosphere containing an active gas which reacts with the cement to form a gaseous aluminum halide, which decomposes in contact with the part depositing metallic aluminum thereon, the active gas containing ZrOClthat decomposes in contact with the part depositing Zr metal thereon, and being formed by vaporizing granules of ZrOClthat are solid at ambient temperature. The part, the cement, and ZrOClgranules are then progressively heated together in a chamber from ambient temperature to the treatment temperature with a plateau at 400&#xb0; C.&#xb1;200&#xb0; C.

Method for forming a protective coating containing aluminium and zirconium on a metal part

The present invention relates to a process for forming on the surface of a metal part a protective coating containing aluminium and zirconium, in which process said part and a cement made of an aluminium alloy are brought into contact with a gas at a treatment temperature in a treatment vessel, the gas comprising a carrier gas and an activator, the activator reacting with the cement to form a gaseous aluminium halide that decomposes on the surface of the part, depositing metallic aluminium thereon, the activator containing a zirconium salt such as Z&#x393;O (&#xbe; obtained from granules of a zirconium salt), disassociation reactions of said zirconium salt taking place within a disassociation temperature range with formation of a Zr metal coating on the surface of the part, the assembly comprising the part, the cement and the zirconium salt granules is progressively heated in the chamber from room temperature up to the treatment temperature, the process being characterized in that the treatment chamber is maintained at an overpressure with no carrier gas flow throughout the temperature range corresponding to the disassociation reactions of the zirconium salt.

Process for forming a protective coating on the surface of a metal part

A method for forming a protective coating containing aluminum on the surface of a metal part, wherein the part is contacted with a carburizer made of an aluminum alloy, at a treatment temperature and in a chamber, the atmosphere of which contains an active gas which reacts with the carburizer to form a gaseous aluminum halide, which decomposes upon contacting the part while depositing aluminum metal thereon. In the method the aluminum alloy of the carburizer includes at least one element, zirconium and/or hafnium, the active gas reacting with the carburizer to also form a halide of the reactive element which decomposes upon contacting the part while depositing the element thereon at the same time as the aluminum.

Method for forming a protective coating containing aluminum on the surface of a metal part

The invention relates to the field of methods of depositing a material on a substrate. It relates to a method of depositing, onto a substrate, a material that acts as a thermal barrier and that prior to deposition is in powder form. The powder is introduced into the plasma jet of a first plasma torch and into the plasma jet of at least one second plasma torch, the first plasma torch and at least the second plasma torch being disposed in an enclosure and oriented in such a manner that their plasma jets cross, so as to create a resultant plasma jet in which the powder is vaporized, the substrate being placed on the axis of the resultant plasma jet.

Method of depositing a thermal barrier by plasma torch

A method of selecting an arrangement of sectors for a turbomachine nozzle is disclosed. The method includes: A) creating a database of three-dimensional numerical models of the sectors by digitizing; B) setting a criterion for selecting an arrangement of sectors and setting a desired value for said criterion, the criterion being a function of the shapes and the relative positions of the sectors; C) for the various arrangements that are evaluated, determining the relative positions of the sectors when assembled together by performing a virtual assembly, and as a function of said positions, determining the value of the selection criterion for the arrangement under evaluation; and D) retaining the arrangement for which the selection criterion has the value closest to the desired value.

Method of selecting an arrangement of sectors for a turbomachine nozzle

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Annecy, France

Justine Menuey