Safran Aircraft Engines

Centre National De La Recherche Scientifique

Université Paul Sabatier (toulouse Iii)

Serge Georges Vladimir Selezneff

Philippe Charles Alain Le Biez

Laurent Paul Dudon

Nicolas Droz

Guillaume Fradet

Lisa Pin

Florence Ansart

Claude Gilbert Jean-Pierre Estournes

Arnaud Louis Gabriel Fregeac

Jean-Baptiste Mottin

Claude Estournes

Hubert Jean-Yves Illand

Ludovic Philippe Liais

Romain Epherre

Franck Bernard Léon Varin

Geoffroy Chevallier

Jacques Chazal Dufour

Fabrice Marsaleix

Michel Lenfant

Patrice Le Bec

Thierry Sacy

A process for manufacturing an abradable layer, includes compressing a powder composition including at least micrometric ceramic particles having a number-average form factor greater than or equal to 3, a mass content of said micrometric ceramic particles in the powder composition being greater than or equal to 85%, the form factor of a particle being defined as the ratio [largest dimension of the particle]/[largest cross-sectional dimension of the particle], and sintering the powder composition thus compressed to obtain the abradable layer, wherein a temperature imposed during sintering, the sintering time and the compression pressure applied are selected so as to obtain a volume porosity rate of the abradable layer greater than or equal to 20%.

Method for manufacturing an abradable layer

An abradable coating for a turbomachine, as well as a turbomachine module and a turbomachine including such an abradable coating, the abradable coating including, with a content of greater than 50% by volume, an inorganic compound whose Mohs hardness is less than 6 and whose melting temperature is greater than 900° C.

Abradable coating

The invention relates to an abradable coating for a turbomachine, comprising a mineral compound having a Mohs hardness of 6 or less and a melting temperature of more than 450° C. or even 800° C., and a polymeric compound with a content of between 40% and 70% by volume.

The present invention relates to a method for continuously manufacturing an abradable sealing element, this element comprising a support substrate covered by a coating comprising at least two successive layers, each comprising a sublayer of abradable material and a sublayer of erosion-control material. This method is noteworthy in that it comprises the steps consisting in: —a) placing at least one support substrate on a rotary carousel around which are placed at least two thermal spray torches enabling the sublayer of abradable material and that of erosion-control material to be deposited, —b) rotating the carousel so as to bring said support substrate successively opposite one then the other of the two torches and to carry out the deposition of the various sublayers and to repeat this operation so as to obtain said sealing element.

Method for manufacturing an abradable sealing element, and abradable sealing element

A process for manufacturing a porous abradable coating includes: filling a mold with hollow glass or thermosetting polymer beads and a slurry; and sintering heat treatment to obtain a ceramic layer with pores. A maximum sintering temperature of the green body of the ceramic part is either higher than the melting temperature of the hollow glass beads so that at the end of the sintering heat treatment the hollow glass beads are melted, or higher than the decomposition temperature of the hollow thermosetting polymer beads so that at the end of the sintering heat treatment the hollow thermosetting polymer beads are decomposed.

Method for manufacturing a porous abradable coating made of ceramic material

An abradable coating for a turbomachine part, includes a matrix made of a first metal material and particles made of a second metal material that are dispersed in the matrix, the first metal material having a melting temperature greater than 900° C., the second metal material having a melting temperature at least 50° C. lower than the melting temperature of the first metal material.

Abradable coating for rotating blades of a turbomachine

An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.

A ring-shaped thermomechanical part for a turbine engine, comprising at least one coating including a polymeric matrix and fillers in non-deflagrating carbon exclusively comprising the chemical element C. A turbine engine comprising such a part.

Ring-shaped thermomechanical part for turbine engine

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

A device applies a coating to a surface of an turbomachine annular casing, wherein the casing has an abradable layer obtained by polymerising a resin. The device includes first support means and, optionally, second automated means movable relative to the first support means. The automated means includes means for depositing said resin on the surface of the casing. The automated means further includes means for spreading the resin on the surface of the casing, and means for unwinding a plastic film that is intended to be interposed between said spreading means and the resin.

Growing community of inventors

Moissy-Cramayel, France

Serge Georges Vladimir Selezneff