Centre National De La Recherche Scientifique

Safran Aircraft Engines

Université Paul Sabatier (toulouse Iii)

Institut National Polytechnique De Toulouse

Snecma

Electricite De France

Universite Toulouse III – Paul Sabatier

Universite Paul Sabatier De Toulouse

Norimat

Universite Paul Sabatier Toulouse III - Upst III

Claude Estournes

Daniel Monceau

Mathieu Boidot

Djar Oquab

Jean-Baptiste Mottin

Juliette Hugot

Romain Epherre

Geoffroy Chevallier

Philippe Charles Alain Le Biez

Serge Georges Vladimir Selezneff

Florence Ansart

Serge Selezneff

Yannick Beynet

Lise Durand

Jean-yves Guedou

Charles Maniere

Pascal Lenormand

Mathilde Rieu

Mohsine Zahid

Nelson Ferreira

Florence Lecouturier

Antoine Lonjon

Yannick Marcel Beynet

Simon Tardieu

Christophe Laurent

David Mesguich

An assembly for densification under load along at least one direction of compression. The assembly includes: at least one volume to be densified having a powdery and/or porous composition and having variations in thickness along the direction of compression; and at least one counter-form of a powdery and/or porous composition, having at least one face facing at least one portion of the volume. The face and each of the portions are separated by at least one deformable interface layer.

Use of a deformable interface for the fabrication of complex parts

A method of fabricating an abradable coating of varying density, and such an abradable coating of varying density. According to the invention, the method comprises the following steps: providing a substrate () having a first portion with its surface situated at a first level (A), and a second portion with its surface situated at a second level (B) different from the first level; depositing a precursor material on the first and second portions of the substrate (); compressing the precursor material between the substrate and a bearing surface; and sintering the precursor material as compressed in this way in order to obtain an abradable coating () having a first portion () on the first portion of the substrate, and possessing a first density, and a second portion () on the second portion of the substrate, and possessing a second density distinct from the first.

Abradable coating having variable densities

The object of the present invention is to produce a metal part equipped with a protection system, particularly for turbine blades for aircraft engines, having a thermal barrier that is improved in terms of thermal properties, adhesion to the part and resistance to oxidation/corrosion. In order to achieve this, the method according to the invention produces in a single step, from specific ceramics, coating layers using SPS technology. According to one embodiment, a metal part is produced according to an SPS flash sintering method and comprises a superalloy substrate (), a metal sub-layer (), a TGO oxide layer () and the thermal barrier () formed by said method from at least two chemically and thermally compatible ceramic layers (). A first ceramic (), referred to as the inner ceramic, is designed to have a substantially higher expansion coefficient. The outer ceramic () is designed to have at least lower thermal conductivity, and a sintering temperature and/or maximum operating temperature that is substantially higher. The thermal barrier () has a composition and porosity gradient () from the metal sub-layer () to the outer ceramic ().

Process for producing a thermal barrier in a multilayer system for protecting a metal part and part equipped with such a protective system

The invention relates to a method for manufacturing a turbine shroud () for a turbomachine, the method comprising manufacturing at least one turbine shroud sector (), positioning the turbine shroud sector () in a bottom mold so that an outer surface of the turbine shroud sector is in contact at least in part with the bottom mold, and depositing a powder layer on an inner surface () of the turbine shroud sector (). Thereafter, a top mold is positioned on the powder layer and an abradable layer () is made by subjecting the powder layer to a method of SPS sintering, the abradable layer () being for being disposed facing a turbine wheel.

Method for manufacturing a turbine shroud for a turbomachine

A method for producing a thermal barrier in a multilayered system for protecting a metal part made of superalloy, by producing a thermal treatment by flash sintering protection materials in layers superposed on the metal part in an SPS machine enclosure. The layers contain, on a superalloy substrate, at least two layers of zirconium-based refractory ceramics. A metal part is produced according to a SPS flash sintering method and contains a superalloy substrate, a metal sub-layer, a TGO oxide layer and the thermal barrier formed by the method. A first ceramic is an inner ceramic designed to have a substantially higher expansion coefficient. An outer ceramic is designed to have at least lower thermal conductivity, and at least one of a sintering temperature or maximum operating temperature that is substantially higher. The thermal barrier has a composition and porosity gradient from the metal sub-layer to the outer ceramic.

The invention relates to a part comprising a coating on a superalloy metal substrate, the coating comprising a metal underlayer covering said substrate, the part being characterized in that said metal underlayer contains a base of nickel aluminide and also contains 0.5 at % to 0.95 at % of one or more stabilizer elements M from the group formed by Cu and Ag for stabilizing the gamma and gamma prime phases.

Part comprising a coating on a superalloy metal substrate, the coating including a metal underlayer

The present invention relates to a method for manufacturing a metal-oxide-based ceramic, including, in order, the step of inserting, into a flash sintering device, a nanocrystalline powder comprising crystallites and crystallite agglomerates of a ceramic of formula, ZrMO, where M is chosen from yttrium, scandium and cerium, or CeM'O, where M&#x2032; is chosen from gadolinium, scandium, samarium and yttrium, where x lies between 0 and 0.2, the powder having an average crystallite size of between 5 and 50 nm, an average crystallite agglomerate size of between 0.5 and 20 &#x3bc;m, and a specific surface area of between 20 and 100 m/g. The invention further includes the step of flash sintering the powder by applying a pressure of between 50 and 150 MPa, at a temperature of between 850&#xb0; C. and 1400&#xb0; C., for a time of between 5 and 30 minutes.

Production of self-supporting ceramic materials having a reduced thickness and containing metal oxides

Growing community of inventors

Rieumes, France

Claude Estournes