Safran

Safran Aircraft Engines

Ngadia Taha Niane

Saïd Boukerma

Ramzi Bohli

David Grange

Didier Maurice Marceau Guerche

Mirna Bechelany

Alain Armel Le Hegarat

Adrien Bernard Vincent Rollinger

Serge Alain Fargeas

Virginie Jaquet

Romain Pierre Cariou

Jean-Claude Marcel Auguste Hanny

Hugues Denis Joubert

Serge Dillenseger

Gilles Martin

Philippe Metron

Serge Tenne

Julien Gelebart

Ming Long

Heni Hachani

Luc Rougier

Didier Dangeul

Camille Mettoux

Loic Galvin

Didier Maurice Guerche

Jean-Claude Marcel Hanny

Said Boukerma

Loïc Galvin

A method for manufacturing a shell mold intended for manufacturing at least one metal part by lost-wax casting, the shell mold including at least one molding cavity intended for molding the metal part, and at least one feed channel intended to convey a liquid metal to the molding cavity, the method including manufacturing a wax pattern including a part pattern intended to form the molding cavity and a feed channel pattern intended to form the feed channel, arranging at least one ceramic insert around at least a portion of the feed channel pattern, and manufacturing the shell mold around the wax pattern.

Method for manufacturing a shell mould for the manufacture of aeronautical metal components by lost-wax casting

A mold for producing a ceramic core by injecting a ceramic composition, the mold having a body in which a casting core cavity is formed, the cavity having a primary cavity and a secondary cavity connected by a plurality of segments, the mold being characterized in that it includes a primary arm configured in such a way as to allow an injection of ceramic composition into the primary cavity, and a secondary arm configured in such a way as to allow an injection of ceramic composition into the secondary cavity, and in that the ratio of the volume of the primary cavity to the volume of the secondary cavity is equal, plus or minus 15%, to the ratio of the volume of the primary arm to the volume of the secondary arm.

Foundry mold for the formation of turbine blade ceramic cores

A method for forming a wax model for the manufacture of turbine blades by lost-wax casting, in which a core is provided, a lower surface shell and an upper surface shell are positioned and bonded on either side of ducts of the core adjacent to the root, the core equipped with the lower surface shell and with the upper surface shell is positioned in an injection mold, wax is injected around the core equipped with the lower surface shell and with the upper surface shell, so as to form a wax model including a blade airfoil and a blade root including a fir tree, the lower surface shell and the upper surface shell being positioned around the core so as to form a portion of the fir tree of the wax model.

Method for forming a wax model for a turbine blade

A process for manufacturing a plurality of single-crystal nozzle sectors each including at least a first blade extending between two platforms by lost-wax casting, includes casting a molten metal into a plurality of ceramic molds distributed in a cluster about an axis, and directional solidification of the cast metal in a furnace comprising a radiant heating element configured to be arranged around the cluster, a solidification front of the metal advancing in each mold in a direction parallel to the cluster axis during directional solidification. Each mold of a second shell separate from a first molding shell of the nozzle sector, which delimits a second cavity for molding a dummy blade acting as a heat shield.

Method for manufacturing a plurality of nozzle sectors using casting

A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

Core for metal casting an aeronautical part

A cluster model and a shell for the production, by lost wax casting, of a plurality of turbomachine elements, are provided. The shell includes a central sprue that is fluidly connected to a casting cup for receiving molten metal; a plurality of shell elements; a plurality of bottom feed conduits for the shell elements; and a handling accessory shell that is independent of the plurality of shell elements and of their metal supply circuit, such that there is no fluid connection to the shell elements. The handling accessory shell is fluidly connected to the central sprue so as to allow top-pour casting of the handling accessory shell.

Cluster model and shell for obtaining an accessory for the independent handling of formed parts and associated method

A directional solidification cooling furnace for metal casting part comprises: a cylindrical internal enclosure having a vertical central axis and a mold support arranged in the internal enclosure; the internal enclosure comprising a casting zone and a cooling zone, the casting zone and the cooling zone being superposed one on the other; the casting and cooling zones being thermally insulated from each other when the mold support is arranged in the casting zone by means of a heat shield that is stationary and by means of a second heat shield that is carried by the mold support; the casting zone including at least a first heating device, and the cooling zone including a second heating device.

Directional solidification cooling furnace and cooling process using such a furnace

A refractory core () for fabricating a hollow turbine engine airfoil () using the lost-wax casting technique, the core comprising a main body () and at least one shell () connected to the main body () and defining a cavity () between the main body and the shell, the shell () being configured to come into contact with the airfoil () during fabrication.

Refractory core comprising a main body and a shell

A ceramic material mold for use in molding a turbine engine blade from a molten metal, the blade including a root, an inner platform, an airfoil, and an outer platform, and the mold including a cavity having the shape of the blade, and an auxiliary grain duct including a first segment and a second segment that is an extension of the first segment, the first segment opening out at one end into a first portion of the cavity forming the root of the blade, and at another end into a second portion of the cavity forming a lip of the inner platform of the blade, the second segment opening out at one end into the second portion of the cavity, and at another end into a third portion of the cavity forming a lip of the outer platform of the blade.

Mold for fabricating a monocrystalline blade by casting, a fabrication installation and method using the mold

A feed system for conveying a molten metal that is to make a casting, the system including a feed channel made of ceramic material that is configured to enable the molten metal to flow by gravity inside the feed channel, the feed channel having a first portion extending in a first direction, and at least one second portion extending in a second direction different from the first direction, the second portion being arranged downstream from the first portion and being connected to the first portion by a junction. The system further includes a damping channel having a first end opening out into the junction and a second end that is closed, the damping channel extending the first portion of the feed channel.

Supply system for supplying a mould with molten metal, and facility and manufacturing method implementing same

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Moissy-Cramayel, France

Ngadia Taha Niane