Safran Aircraft Engines

Safran

Vincent Marc Herb

Joseph Toussaint Tami Lizuzu

Matthieu Jean Luc Vollebregt

Coralie Cinthia Guerard

Serge Alain Fargeas

Adrien Bernard Vincent Rollinger

Patrick Emilien Paul Emile Huchin

Daniel Quach

Sebastien Digard Brou De Cuissart

Sébastien Digard Brou De Cuissart

Ramzi Bohli

Didier Maurice Marceau Guerche

Jean-Claude Marcel Auguste Hanny

Pascal Francis Patrick Gomez

Laetitia Nicole Person

Chantal Sylvette Marie-Noël Langlois

Chantal Sylvette Langlois

Mathieu Jean Luc Vollebregt

Jun Ni

Francois Casteilla

Adrien Bernard Rollinger

Mathieu Jean Vollebregt

Didier Maurice Guerche

François Casteilla

The invention provides a method of assembling together a first core () and a second core () in order to make a non-permanent model configured for use in lost wax molding to form a part having a first cavity and a second cavity corresponding respectively to the first core and to the second core. The invention is characterized by the fact that the first and second cores () are assembled together with a first spacer (), the first spacer () being arranged between the first and second cores.

Method for creating a nonpermanent model

The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

Turbomachine blade cooling circuit

A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.

Core for manufacturing a turbomachine blade

A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.

Method for manufacturing a two-component blade for a gas turbine engine and blade obtained by such a method

Growing community of inventors

Moissy-Cramayel, France

Vincent Marc Herb