Safran

Safran Aircraft Engines

Snecma

Safran Landing Systems

Thierry Patrick Chauvin

Michel Wlasow Wlasowski

Kris Hoes

Dominique Marie Christian Coupe

Nicolas Pierre Lanfant

Franck Bernard Leon Varin

Jérôme Olhagaray

Raoul Jaussaud

Nicolas Cambyse Ashtari

Adrien Touze

Sylvain Didier Leclercq

Olivier Foussard

Quentin Roirand

Emilie Goncalves

Marc-Emmanuel Jean François Techer

Nicola Piccirelli

Franck Bernard Léon Varin

Nicolas Tran

Lionel Christian Jean-Loïc Gay

Pierre-Antoine Bossan

Lauren Chin

Cali Lapenta

Benoît Bazin

Samuel Louis Marcel Marie Maillard

Loïc Sorgnard

Nate Gravelle

Benoit Bazin

Philippe Gallois

Thomas Bernd Paulo Viassone

Florence Castagnet

Franck Bernard Varin

The invention relates to a curing mold () for manufacturing a turbomachine component made of composite material from a preform (), comprising: —a first and a second body () defining an air gap receiving the preform; —at least one primary channel () arranged in the first and/or the second body; —an injection member () of a pressurized fluid in the primary channels; —at least one secondary channel (), in which a piston () slides, which delimits, on the one hand, a first chamber () in communication with the or a primary channel and, on the other hand, a second chamber () in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.

Curing mold for manufacturing a turbomachine component made of composite material from a preform and method for producing a component by means of such a mold

A tooling for winding a fibrous fabric on a support, allowing gradual modification of the shape of the support as winding progresses, and includes compaction devices to reduce wrinkling of the fabric obtained after compaction.

Machinery for winding a fibrous textured material, and associated winding method

A curing mold for manufacturing a turbomachine component is made of composite material from a preform, including: a first and a second body defining an air gap receiving the preform; at least one primary channel arranged in the first and/or the second body; an injection member of a pressurized fluid in the primary channels; at least one secondary channel, in which a piston slides, which delimits, on the one hand, a first chamber in communication with the or a primary channel and, on the other hand, a second chamber in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.

A curing mold for manufacturing a turbomachine part made of composite material from a preform produced by draping pre-impregnated materials includes: a first body and a second body designed to be attached to each other and jointly defining a fixed air gap for receiving the preform and itself including a molding part of complementary shape with the part to be manufactured and intended to receive a portion to be molded of the preform, and at least one additional part located in a peripheral space of the air gap and intended to receive an additional portion forming an edge of the preform; a heating member designed to heat the preform in the air gap to a first temperature; at least one inflatable bladder housed in the first or second body, facing an additional part of the air gap; a member for injecting a pressurized fluid inside the bladder(s).

Curing mold for manufacturing a turbomachine component made of composite material from a preform and method for manufacturing a component by means of such a mold

The invention relates to a resin injection regulator for a resin injection circuit in a mould for producing a composite part, in particular a turbine engine composite part, characterised in that it comprises at least one vessel which is connected to said circuit and inside of which a movable wall means can be moved in a sealed manner, said movable wall means defining in said vessel a first cavity which forms a container for accumulation of resin and is designed to be connected to at least one part of said circuit, and a second cavity which is designed to be connected to a source of pressurised fluid, said movable wall means being designed to be urged by the pressurised fluid with which the second cavity is supplied in order to exert a pressure on the resin contained in the first cavity by isolating said resin from said fluid.

Resin injection regulator, resin injection circuit and associated methods

A method for analysing a bonding between two aeronautical parts. The method includes the steps of a) applying a release agent to a first surface to be bonded of a first part and to a second surface to be bonded of a second part, b) applying an adhesive to at least one of the first and second surfaces and positioning these surfaces on top of each other, the adhesive forming an adhesive film after polymerisation, c) separating the parts from each other and removing the adhesive film in one piece, d) analysing the adhesive film. The invention also relates to a method for bonding two aeronautical parts.

Methods of bonding two aeronautical parts and of analysing a bonding between two aeronautical parts

The invention relates to an injection mold () for manufacturing a rotary part made of a composite material having outer flanges, comprising a mandrel () on which a fiber reinforcement is intended to be held () and including a central wall () the profile of which matches that of the part to be manufactured and two side plates (), molding wedges () for bearing against a non-covered surface of the fiber reinforcement, and two outer bells () for covering the molding wedges and the plates of the mandrel with sealing O-rings () being inserted between the bells and the plates of the mandrel, the bells each being provided with an attachment flange () for bearing against one another with at least one sealing O-ring () inserted therebetween, the attachment flanges of the bells being clamped against one another.

Injection mould for manufacturing a rotary part made of a composite material having external flanges, in particular of a gas turbine casing

A tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, the tooling including a blade support for receiving a blade while leaving surfaces of the leading edge of the blade disengaged; and a leading edge reinforcement support on which the blade support is designed to be mounted, and including two lateral wedges between which the metal reinforcement for the leading edge of the blade is positioned, the wedges being suitable for being capable of moving towards each other and apart from each other and each of them being provided with a suction grid for gripping the metal reinforcement, the leading edge reinforcement support further including heater elements for polymerizing an adhesive film applied on the leading edge surfaces of the blade.

Tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, and a method using such tooling

A mold includes a first shell and a second shell that are suitable, in the closed position, for imparting a shape to a part that is to be molded in the mold, a main axis being perpendicular to the main plane in which the first shell and the second shell extend. The mold further includes a slide that is situated between the first shell and the second shell and that is in contact with the first shell and the second shell when the mold is in the closed position, and that is to come into contact with the molded part, the slide presenting a first face that constitutes its interface with the first shell, the first face presenting a primary direction along which the slide is suitable for sliding along the first face when the mold is in the open position.

Mold comprising shells and at least one slide

Growing community of inventors

Moissy-Cramayel, France

Thierry Patrick Chauvin