Centre National De La Recherche Scientifique

Safran Aircraft Engines

Université Paul Sabatier (toulouse Iii)

Norimat

Romain Epherre

Jean-Baptiste Mottin

Philippe Charles Alain Le Biez

Serge Georges Vladimir Selezneff

Florence Ansart

Claude Estournes

Geoffroy Chevallier

Yannick Beynet

Yannick Marcel Beynet

Pascal Lenormand

This invention relates to a method for manufacturing a part of complex shape () by successive deposition of layers according to a technique of 3D additive printing and pressure sintering, comprising the following steps: an initial step of producing a model () from a material chosen from a porous or pulverulent material based on a metal alloy, a ceramic, a composite material and a lost material by formation of successive layers deposited according to the digitally controlled 3D additive printing technique, followed by a step of introducing a preform () made of porous or pulverulent material to be densified, derived from the model (), into a mold () filled with a sacrificial porous or pulverulent material () in addition to the preform (), the uniaxial densifying pressure sintering () then being applied to the mold () in order to form the part () which is finally extracted from the mold ().

Method for manufacturing a part of complex shape by pressure sintering starting from a preform

A method for producing a counter-form () for manufacturing a part having a complex shape () by pressure sintering densification. The counter-form () is formed from successive layers produced by numerically-controlled three-dimensional (3D) additive printing according to the following steps: numerically recording a three-dimensional negative of the part to be produced () in a control unit of a three-dimensional additive printing system in order to constitute the positive form of the counter-form to be produced; producing the counter-form () using a 3D additive printing technique. The part having a complex shape () is then manufactured by pressure sintering, then separated from the counter-form which is also sintered ().

Method for producing a counter-form and method for manufacturing a part having a complex shape using such a counter-form

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 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

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Toulouse, France

Romain Epherre