Snecma

Safran Aircraft Engines

Safran

Daniel Quach

Jean-Louis Martial Verger

Patrick Pourfilet

Matthieu Jean Luc Vollebregt

Patrick Wehrer

Yvon Marie-Joseph Louesdon

Philippe Bouthemy

Joseph Toussaint Tami Lizuzu

Jean-Claude Marcel Auguste Hanny

Pascal Francis Patrick Gomez

Serge Dillenseger

Adrien Bernard Vincent Rollinger

David Locatelli

Patrick Emilien Paul Emile Huchin

Christian Bariaud

Serge Prigent

Dominique Coyez

Coralie Cinthia Guerard

Damien Alquier

Vincent Marc Herb

Franck Edmond Maurice Truelle

Christian Defrocourt

Laetitia Nicole Person

Florian Le Merdi

Alain Grandin

Pascal Gomez

Didier Legeai

Umberto Aprile

Philippe Chabaneix

Claude Baldassari

Dominque Coyez

Joseph Tami

Fadoua Cisse

Chantal Sylvette Langlois

Sabine Maltaverne

Isabelle Marie Monique Valente

Joseph Tami-Lizuzu

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 fabrication method for fabricating a pattern for lost pattern casting, comprising at least one insert (), providing at least two pattern portions (), said at least two portions being made of a material that can be eliminated, and assembling said at least two pattern portions together around at least a portion of said at least one insert in sealed manner so as to make said pattern ().

Method for producing a pattern for lost pattern casting

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 invention relates to the field of casting, and more particularly to a method of producing a ceramic core () for casting, said core () presenting a shape that includes at least a first lateral protuberance (), and the method comprising at least a step of injecting a paste comprising a ceramic granulate and a polymer binder into a mold cavity In order to form a part () presenting a shape corresponding to the shape of the core () together with at least one additional lateral protuberance () adjacent to said first lateral protuberance (), a step of firing the part (), and a step of eliminating said additional lateral protuberance () from the part () after said firing step.

Method for producing a ceramic core

A method for manufacturing a turbine engine blade including an airfoil with a profile defined by a theoretical digital model, the method including: manufacturing a blank having a thickened portion along a trailing edge of the airfoil relative to the theoretical profile; removing the thickened portion by adaptive machining, including: positioning the blank in a reference frame; acquiring, by probing at a predetermined number of points on a first surface of the blank along the trailing edge, positions of the points in the reference frame; determining differences, in one direction, in position from corresponding points of the theoretical model; producing machining grids on the blank surface, peaks of the grids determined from the points; determining an amount of material to be removed from the surface of the grids, based on the position of the points relative to the peaks and the deviations in position; and machining the airfoil.

Method for machining the trailing edge of a turbine engine blade

A tooling for fabricating a foundry core, for making a circuit for cooling a blade of a turbine engine, the tooling including: a mold for injecting a paste and including imprints for a first portion and a second portion of the core; a mechanism bearing against and/or engaging end portions of a ceramic rod that interconnects the portions of the core and that passes through the imprint for the first portion of the core; and a support mechanism in the imprint for the first portion of the core to support a substantially middle portion of the rod.

Tool for manufacturing a foundry core for a turbine engine blade

A method for finishing a shape of a component by machining, in which one area is produced by smelting with a thickened portion forming a first surface with a surrounding profile and a theoretical profile defined by a second surface, the method including: defining, on the second surface, a grid forming nodes and squares; defining each point over which the machining tool is to pass according to weighting coefficients equal to weight to be given to the nodes of the square in which the tool is located, to be the barycenter of assigned nodes of the coefficients; measuring, for each node located outside an outer limit, the delta between the first surface at the node and the theoretical position of the node; calculating deltas for each node within the outer limit by interpolation from already known deltas; using the weighting coefficients, defining the delta to be applied at each point.

Adaptive machining method for smelted blades

A tooling for injection-molding a part, the tooling including two cavity blocks each including a cavity formed therein of a shape corresponding to a shape of a part that is to be molded once the cavity blocks have been superposed. At least one of the cavity blocks includes a mechanism for positioning a core, which mechanism includes at least one bearing surface for bearing against the core and at least one presser screw screwed into a threaded passage of the cavity block for purpose of holding the core in position against the bearing surface. The tooling further includes a force-limiter limiting force applied to the core by the presser screw.

Device for injection-moulding a part

A mold for producing a part, such as a turbomachine blade model, by injecting wax into a cavity, the cavity including at least two cavity elements, each of which is supported in a cavity block. The two cavity blocks are mobile relative to one another between a closed position for injecting the wax and an open position for removing the part following the injection of the wax. The two cavity blocks are mobile in a horizontal plane.

Mold for producing parts by wax injection

A tooling for injection-molding a part, the tooling including two cavity blocks each including a cavity formed therein of a shape corresponding to a shape of a part that is to be molded once the cavity blocks have been superposed, at least one of the cavity blocks including an ejection mechanism ejecting the molded part and including at least one ejector movable between a molding position and an ejection position. The ejector is guided to move between its two positions along a curved path, or a circular arc, of shape that corresponds to a shape of a portion of the mold part to be extracted from the cavity.

Tooling for injection-molding a part

An injection mold producing a model of a turbine engine blade, including: a top surface that folds onto a bottom surface, both surfaces including long rods for supporting a core generating cooling cavities inside the blade, wherein the long rods of the bottom surface are configured to contact a first surface of the airfoil at bearing points, and the long rods of the top surface are configured to contact a second surface of the airfoil at clamping points; at least one short rod extending from one of the surfaces of the mold and pointing towards a false point located on one of the surfaces of the airfoil, the length of the short rod being shorter than the distance between the surface of the mold and the surface of the blade at the false point, and the difference between the length and the distance being equal to tolerance in relation to positioning of the false point in event of deformation of the core.

Injection mold for a wax model of a turbine blade having an isostatic core holder

A method for deburring a ceramic foundry core obtained by injecting a ceramic paste, the paste including a binder having a predetermined glass transition temperature, into a mold and having at least one surface portion with a surplus of material forming a burr to be eliminated. The method includes the following stages: a) disposing and attaching the molded, unfired foundry core onto a mounting; b) placing a milling tool, having an elongated shape with a helically cut edge, onto a tool holder; c) causing the tool to rotate around its axis and touching the milling tool to the surface portion to be deburred; and d) freezing the surface portion to be deburred such that the foundry core is maintained at a temperature lower than a glass transition temperature during the deburring operation.

Method for deburring a ceramic foundry core

Growing community of inventors

Fontenay Sous Bois, France

Daniel Quach