Safran Aircraft Engines

Safran

Snecma

Jean-Claude Marcel Auguste Hanny

Matthieu Jean Luc Vollebregt

Daniel Quach

Joseph Toussaint Tami Lizuzu

Pascal Francis Patrick Gomez

Adrien Bernard Vincent Rollinger

Patrick Emilien Paul Emile Huchin

Christian Bariaud

Renaud James Martet

Patrick Joseph Marie Girard

Ngadia Taha Niane

Philippe Jean-Pierre Pabion

David Grange

Saïd Boukerma

Coralie Cinthia Guerard

Dominique Coyez

Vincent Marc Herb

Serge Dillenseger

Sami Kelim Benichou

Philippe Metron

Stephanie Dominique Roger

Laetitia Nicole Person

Julien Gelebart

Olivier Charles Henri Massy

Renaud Martet

Stéphanie Dominique Roger

Sami Benichou

An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.

Assembly for manufacturing a turbine engine blade

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 method for manufacturing a turbine engine blade () comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade () comprising a tip (S) with a closing wall () joining the pressure side and suction side walls in the region of this tip (S) in order to define a well shape, the closing wall including through-holes. The closing wall () obtained by moulding has a considerable nominal thickness with pits () locally reducing this thickness at each through-hole in order to facilitate the removal by chemical etching of alumina rods defining the holes. Since the closing wall () thus has a large nominal thickness, it can then be machined in order to form raised patterns or complex shapes inside the well.

Method for manufacturing a turbine engine blade including a tip provided with a complex well

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

The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point Psituated on the suction face of the airfoil upstream of the suction face neck and a point Psituated on the pressure face of the airfoil upstream of the pressure face neck.

Turbomachine blade that is cast with a local fattening of the section of the airfoil

Growing community of inventors

Moissy-Cramayel, France

Jean-Claude Marcel Auguste Hanny