Safran Ceramics

Safran Aircraft Engines

Safran

Thierry Guy Xavier Tesson

Christophe Paul Aupetit

Lucien Henri Jacques Quennehen

Marie Lefebvre

Stéphane Roger André Goujard

Maxime François Roger Carlin

Philippe Avenel

David Mathieu Paul Marsal

Eric Philippe

Matthieu Arnaud Gimat

Nicolas Eberling-Fux

Adrien Delcamp

Ramzi Bohli

Gaël Frédéric Claude Cyrille Evain

Clément Marie Benoît Roussille

Cédric Descamps

Thomas Revel

Aline Planckeel

Hubert Jean-Yves Illand

Gilles Gérard Claude Lepretre

Rémy Dupont

Simon Thibaud

Charles Leleu

Eddy Goullianne

Thierry Jacques Albert Le Docte

Emilie Lesizza

Nicolas Eberling-fux

Lucas Mathoux-Heuls

Denis Jean Armel Busquet

Christophe Jean François Thorel

Gaël Bouchy

Cécile Marie Emilienne Chevalier

An installation for sintering a preform includes a sintering furnace in which a load is disposed, wherein the load includes a revolution preform disposed around at least one holding tool, the at least one holding tool including a disk and a crown present on the periphery of the disk, the crown being made of compressible material capable of being eliminated by thermal oxidation, a portion of the preform being in contact with the crown before sintering.

Holding tools for preform sintering

An assembly for a turbomachine optimizes air flow near the exhaust cone which has an outer annular wall for the flow of a primary air flow and an inner annular wall arranged inside the outer annular wall, a metal casing arranged upstream of the exhaust cone, a shroud defining a radially inner face with respect to the primary air flow, and a metal connecting flange interposed longitudinally between the inner annular wall and the metal casing and connecting the inner annular wall and said metal casing. The assembly includes at least one bolt which passes through the outer annular wall and the annular portion of the connecting flange, a nut screwed onto the bolt and arranged radially inside the annular portion of the connecting flange, and at least one spacer which has a coefficient of expansion that is greater than the coefficient of expansion of the metal casing.

Assembly for an exhaust cone in a turbomachine nozzle

An assembly for a turbomachine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. The bolt includes a support member having an annular collar mounted between the screw or the nut, and the first part. The collar has a support surface abutting, at least partially, on a complementary support surface of the first part. The collar also includes a recessed annular groove extending at the inner periphery of the collar.

Assembly for a turbomachine

The invention relates to a three-dimensionally woven multilayer fibrous structure () having the same number of warp yarns woven at any level along the warp direction, the fibrous structure () comprising, in the warp direction, a first part () and a second part (), the first part () having a thickness measured in a direction perpendicular to the warp and weft directions, greater than the second part (), characterised in that the spacing between two weft planes along the warp direction is greater in the second part than in the first part (), and in that the number of weft yarns is lower in the second part () than in the first part ().

Method for manufacturing a ring sector

A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.

Consolidation method using gas phase infiltration

The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone () comprising a radially outer annular wall () defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (), the sound box comprising a radially inner annular wall (), —a connecting member () intended to be axially inserted between the exhaust housing and the ejection cone (), the connecting member () comprising an upstream annular flange () intended to be attached to the exhaust housing and a plurality of downstream securing tabs () connected to the inner annular wall (), —an annular sealing shroud () comprising an upstream portion surrounding the securing tabs () of the connecting member () so as to cover the spaces circumferentially located between the securing tabs () and axially located between the upstream annular flange () of the connecting member () and the radially inner annular wall ().

Sealing assembly for a turbine ejection cone

Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps:

Method for manufacturing a part made from CMC

A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.

Process for manufacturing a fibrous preform for reinforcement of parts made of composite material with a high local variation in thickness

An assembly for a turbomachine turbine includes a housing () extending circumferentially about an axis X, sectors () intended to form a ring capable of delimiting a gas flow path, each sector () comprising a first side () and a second side () extending radially and circumferentially about the said axis X and spaced axially from each other, each side () of the sector () including at least one radial bearing surface of an oblong hole capable of cooperating with support pins () of the housing (), at least one of the sides () including means () for the circumferential positioning of the sector () with respect to the housing (), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.

Assembly for a turbomachine turbine

A method for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.

Method for producing a consolidated fiber preform

An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially.

Assembly for a spreader connection between a turbine casing and a turbine engine ring element

A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially &#x3c0; shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.

Growing community of inventors

Moissy-Cramayel, France

Thierry Guy Xavier Tesson