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Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Office National D'etudes Et De Recherche Aerospatiales (Onera)

Societe Sochata

Centre National De La Recherche Scientifique

Université Paul Sabatier (Toulouse III)

Institut National Polytechnique

Andre Hubert Malie

Christophe Chaput

Bertrand Saint-Ramond

Isabelle Porte

Cyrille Delage

Pierre J Josso

Sarah Hamadi

Serge Alexandre Alperine

Jean-Paul Fournes

Pascal Fabrice Bilhe

Jacques Louis Leger

Annie Pasquet

Jean-Pierre Huchin

Michel Grosbras

Marie-France Beaufort

Frederic Jacquot

Denis Georges Manesse

Marie-Ange Boheas

Helene Cerda

Remy Mevrel

An estimation method for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on a support tooling, the method including: digitally modeling a geometrical shape of the hot part and its movements relative to the target; representing the modeled hot part as a surface mesh; and estimating, for at least one mesh element of the hot part exposed to the radiation from the target during deposition of the coating, a coating thickness to be deposited on the mesh element at a given instant by using a radiation model modeling radiation from the target and taking account of the position of the mesh element at that given instant relative to the target.

Method and device for estimating a thickness of a ceramic thermal barrier coating

The invention relates to a composite target in the form of a bar made of ceramic powders and designed to be evaporated under an electron beam, the target comprising zirconia and at least one zirconia stabilizer. In characteristic manner, said target is wherein said zirconia stabilizer is at a molar content lying in the range 2% to 30% and wherein said zirconia is formed by more than 90% of a monoclinic phase. The invention is applicable to fabricating a ceramic thermal barrier of low thermal conductivity and high thermomechanical strength formed by evaporation under an electron beam.

Target for vaporizing under an electron beam, a method of fabricating it, a thermal barrier and a coating obtained from a target, and a mechanical part including such a coating

A composite target is placed in a chamber. The target is in the form of a bar made of ceramic powder and it presents composition that is not uniform in the longitudinal direction. At least one substrate is introduced into the chamber in order to have formed thereon a ceramic coating with a composition gradient. The top face of the bar is swept by an electron beam so as to melt the bar material at its top face and form a vapor cloud in the chamber under low pressure. A bar is used that presents a plurality of superposed layers of different compositions, with the composition within each layer being uniform over the entire cross-section of the bar. Each layer of the bar comprises zirconia and at least one oxide selected from the oxides of nickel, cobalt, iron, yttrium, hafnium, cerium, lanthanum, tantalum, niobium, scandium, samarium, gadolinium, dysprosium, ytterbium, and aluminum.

Method of forming a ceramic coating on a substrate by electron-beam physical vapor deposition

A method of diffusion brazing parts made of a superalloy A uses a single-component brazing powder prepared by measuring a quantity of a superalloy powder having a composition identical to the superalloy A and a quantity of a boron and/or silicon flux powder in a proportion of between 0.1% and 40% by weight of the superalloy powder, mixing the powders and placing them with balls made of superalloy A in a container also made of superalloy A, closing the container and keeping its contents in a controlled atmosphere, placing the container in a grinder and operating the grinder to keep the container moving for a period ranging from 30 seconds to 500 hours in order to encrust the flux onto the surface of the grains of the superalloy powder.

Method of diffusion brazing superalloy parts

A thermal barrier coating for a superalloy part used, in particular, in turbomachines comprises a ceramic coating and a sub-layer interposed between the superalloy substrate and the ceramic coating, the sub-layer being composed of a nickel and/or cobalt aluminide containing at least one platinum-like metal and at least one metal for promoting the formation of a layer of oxide constituted by the alpha-allotropic variety of alumina.

Thermal barrier coating with improved sub-layer and parts coated with

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Targe, France

Andre Hubert Malie