Safran

Safran Aircraft Engines

Snecma

Societe De Motorisations Aeronautiques

Hugues Denis Joubert

Patrice Eneau

Adrien Bernard Vincent Rollinger

Amar Saboundji

Charlotte Marie Dujol

Luc Bianchi

Ngadia Taha Niane

Sylvain Paquin

Chantal Giot

Benjamin Sauthier

Philippe Picot

Heni Hachani

Ming Long

Stéphan Daux

Stephan Daux

Sébastien Ferrari

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 component includes a substrate at least a portion of which adjacent to a surface of the substrate is made of a material including silicon; a bond coat located on the surface of the substrate and including silicon, an environmental barrier which includes an outer layer of ceramic material covering the bond coat, wherein the environmental barrier further includes a self-healing inner layer located between the bond coat and the outer layer, the inner layer including a matrix in which silico-forming particles are dispersed, these particles being capable of generating a matrix crack healing phase in the presence of oxygen.

Component protected by an environmental barrier

A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.

Ceramic core for a multi-cavity turbine blade

A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.

Gas turbine blade cooling circuit having a cavity with a high aspect ratio

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Paris, France

Hugues Denis Joubert