Safran

Safran Nacelles

Safran Aero Boosters Sa

Centre National De La Recherche Scientifique

Safran Aircraft Engines

Université Paris Est Creteil Val De Marne

Centre National De La Recherche Scientifique-Cnrs

Pierre Jean Sallot

Rabih Khazaka

Toni Youssef

Aurelie Soula

Yann Jean-Pierre Lefaux

Jean-Michel Patrick Maurice Franchet

Luc Bianchi

Mirna Bechelany

Aurélien Joulia

Nicolas Tran

Clara Desgranges

Anne-Laure Rouffie

Jonathan Cormier

Jean-Philippe François Couzinie

Guy Dirras

Ivan Georges Guillot

Loic Perriere

Mathilde Madeleine Louise Laurent

Thomas Philippe Joseph Rieger

Jean-Marc Eric Joubert

Patrick Villechaise

Baptiste Joël Christian Fedi

Gilbert Leconte

Elodie Marthe Bernadette Drouelle

Sylvain Pierre Dubois

Véronique Brunet

A method for manufacturing a power electronic module by additive manufacturing includes the step of depositing a layer of an electrically conductive nanoporous material on a substrate that includes an electrically insulating layer and at least one layer of conductive metal material, called a metallized substrate. The method further includes the step of placing an element, for example an active component of the semiconductor power component type, on the layer of nanoporous material and sintering the layer of nanoporous material, so as to ensure a mechanical and electrical connection between said element and the metallized substrate.

Method for manufacturing an electronic power module

A method for manufacturing a metal bladed wheel of a turbomachine reinforced by an insert made of metal matrix composite material, includes winding the ceramic fibers around a mandrel in order to form the insert, the ceramic fibers being surrounded by a material constituting the matrix; and spark plasma sintering the insert with a powder of metal constituting the bladed wheel to be manufactured.

Method for manufacturing a composite turbomachine bladed disk (BLISK) with ceramic reinforcement

A method for manufacturing a blade for a turbine engine, including a root connected to a vane extending in a longitudinal direction, includes providing an assembly having a first part intended to form a root of the blade and a projecting second part projecting in the longitudinal direction from the first part; providing a mold comprising a first impression and a second impression delimiting together a cavity, said cavity comprising a first space and a second space; arranging the first part in the first space of the cavity and the second part in the second space of the cavity; and forming a third part by injecting an aluminium-based alloy in the cavity.

Method for manufacturing a blade for a turbomachine

A metal part with a wall thickness less than 5 mm includes a preform made from a flexible composite sheet, a flexible composite sheet segment, and an appended insert including a fastening portion that is sandwiched between a rear end of the preform and the flexible composite sheet segment. The flexible composite sheet segment encloses the fastening portion of the appended insert.

Method for making a metal part with a complex geometry with a thin wall

The invention relates to a method for manufacturing a power electronic module () by additive manufacturing, characterized in that it comprises the steps of:

Method for manufacturing an electronic power module using polymer preforms

A coated part includes a metallic substrate, a thermal barrier comprising a ceramic material and covering the metallic substrate, wherein the coated part further includes a protective coating covering the thermal barrier, the protective coating including, in a first region, a first MAX phase, denoted PZ2, of formula (ZrTi)AlC or a first MAX phase, denoted PC2, of formula (CrTi)AlC with x non-zero and less than or equal to 1 in the MAX phases PZ2 and PC2, and the protective coating includes, in a second region covering the first region, a second MAX phase of formula TiAlC.

Coated part comprising a protective coating based on MAX phases

A part made from a composite material having a ceramic matrix and including a protection device, the protection including a coating layer having a gradual composition. The gradual-composition coating layer includes at least one silicon phase and one aluminium phase, the proportions of which change according to the height in the layer, with a first height in the gradual-composition coating layer corresponding to a silicon-free composition, and a second height corresponding to an aluminium-free composition. A method for producing such a protection, and to a device for carrying out the method, are disclosed.

Part comprising a protective coating having a gradual composition

Casting core for the manufacture of hollow metal aeronautical parts, in particular high-pressure turbine parts by lost-wax casting, including a composite material including on the one hand a first phase of formula MAlC, where n=1 to 3 and M being a transition metal selected from the group consisting of titanium and/or niobium and/or molybdenum, the composite material including on the other hand a second phase of formula AlC.

Foundry core for manufacturing a hollow metal aeronautical part

A method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in a casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10m/s in the drawing direction. The present disclosure also relates to a plant having one or more devices for implementing the method.

Method for obtaining a product made of titanium alloy or a titanium-aluminium intermetallic compound

A casting ring having a first section made of a heat-conductive material and a second section made of a MAX phase alloy material, and a method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in the casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10m/s in the drawing direction.

Casting ring for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic alloy and method using same

A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.

Method for manufacturing a turbine engine vane

A method for manufacturing an integrally formed bladed disk of a turbomachine, includes manufacturing a plurality of blades, the blades including a root and a profiled portion; and spark plasma sintering the blades with a metal powder, the blades being angularly distributed over a contour of an annular spark plasma sintering mold, the root of the blades being embedded into the metal powder, the profiled portion of the blades protruding from the metal powder radially outwardly.

Solution for manufacturing a one-piece bladed disc

A nickel-based superalloy includes, in atomic percentages, 13% to 21% chromium, 15% to 26% cobalt, 4% to 8% aluminum, 4.5% to 8% titanium, 8% to 18% iron, boron in an atomic percentage less than or equal to 0.5% or no boron, carbon in an atomic percentage less than or equal to 1% or no carbon, at least one additional element selected from molybdenum, tungsten, tantalum and niobium, a total atomic content of the at least one additional element being less than or equal to 1.5% or no such at least one additional element, the remainder being nickel and unavoidable impurities, with a sum of the atomic percentages of aluminum and titanium being comprised between 8.5% and 15%. The novel superalloy composition has a limited density and exhibiting, when hot, good mechanical properties as well as good resistance to oxidation and corrosion.

Superalloy with optimized properties and a limited density

A method for producing a thin-walled metal part with complex geometry includes mixing a metal powder with a polymer binder in order to obtain a composite mixture, producing a flexible composite sheet from the composite mixture, cutting, in the flexible composite sheet, a preform based on a contour of the metal part, applying the preform in a mold having a surface configured with a relief of the metal part, and debinding and sintering the preform in order to obtain the metal part.

A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

Growing community of inventors

Moissy-Cramayel, France

Pierre Jean Sallot