Safran Aircraft Engines

Centre National De La Recherche Scientifique

Université Paul Sabatier (toulouse Iii)

Snecma

Safran Aero Boosters Sa

Philippe Charles Alain Le Biez

Serge Georges Vladimir Selezneff

Nicolas Droz

Serge Selezneff

Michael Podgorski

Ludovic Edmond Camille Molliex

Lisa Pin

Florence Ansart

Claude Gilbert Jean-Pierre Estournes

Arnaud Louis Gabriel Fregeac

Jean-Baptiste Mottin

Laurent Paul Dudon

Claude Estournes

Célia Iglesias Cano

Ludovic Philippe Liais

Romain Epherre

Franck Bernard Léon Varin

Geoffroy Chevallier

Pierre Marie Montfort

Lionel Marcin

Thierry Sacy

Nicolas Cornacchia

Jacques Chazal Dufour

Fabrice Marsaleix

Michel Lenfant

Patrice Le Bec

Pierre-Marie Montfort

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

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 method of fabricating an abradable coating of varying density, and an abradable coating of varying density. The method comprises the following steps: providing a substrate having a first portion and a second portion; depositing a first precursor material on the first portion of the substrate; compressing the first precursor material between the substrate and a first bearing surface; sintering the first precursor material as compressed in this way in order to obtain a first abradable coating portion on the first portion of the substrate, and possessing a first density; depositing a second precursor material on the second portion of the substrate; and compressing the second precursor material between the substrate and a second bearing surface.

Abradable coating having variable densities

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

The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughness.

Abradable coating made of a material having a low surface roughness

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.

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.

Device for coating a turbomachine annular casing

A corrosion-resistant abradable covering to adhesively bond to a wear portion of a structural part, the covering including at least a polyester-based matrix and an aluminum alloy filler that are molded together.

Corrosion-resistant abradable covering

An annular turbine engine stator portion including a structural support provided in succession with a bonding underlayer and with an abradable coating formed by a resin filled with microbeads, the bonding underlayer for fastening the abradable coating to the structural support being formed by fiber reinforcement made of long fibers having a peripheral portion of the reinforcement that is secured to the structural support and having a central portion thereof that is impregnated with the resin filled with microbeads while the abradable coating is being fastened to the structural support.

Growing community of inventors

Draveil, France

Philippe Charles Alain Le Biez