Safran Aircraft Engines

Snecma

Safran

Patrick Emilien Paul Emile Huchin

Matthieu Jean Luc Vollebregt

Sébastien Digard Brou De Cuissart

Serge Alain Fargeas

Marc Soisson

Coralie Cinthia Guerard

Valéry Piaton

Anthony Texier

Karine Deschandol

Christian Bariaud

Joseph Toussaint Tami Lizuzu

Sami Kelim Benichou

Stéphanie Deflandre

Patrice Eneau

Adrien Bernard Vincent Rollinger

Charlotte Marie Dujol

Daniel Quach

Mirna Bechelany

Jean-Claude Marcel Auguste Hanny

Pascal Francis Patrick Gomez

Patrice Jean-Marc Rosset

Vincent Marc Herb

Laetitia Nicole Person

Coralie Geurard

Thierry Henri Raymond Alaux

Boris Soulalioux

The invention relates to a method for manufacturing a turbine engine blade () including an active-surface wall () and a passive-surface wall () separated from one another, this blade () including a tip that has a closing wall grouping together the active-surface () and passive-surface () walls in the region of this tip to define the bottom () of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom () of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition () supported by the bottom thereof ().

Method for manufacturing a blade comprising a bathtub tip integrating a small wall

A method is for positioning a hollow workpiece obtained by casting and that enables the workpiece obtained in this way to be machined in accurate manner. The workpiece is obtained by a casting method involving a mold and a sacrificial core inserted inside the mold and serving to form at least one cavity in the workpiece. The workpiece includes surfaces of a first type defined during casting by the surfaces of the mold, and surfaces of a second type defined during casting by the surfaces of the core. A frame of reference for positioning the workpiece is constructed that includes at least three reference points (P-P) belonging to surfaces of the second type of the workpiece.

Method of positioning a hollow workpiece

A core for the moulding of a turbine engine blade, this blade including a vane extending along a spanwise direction and ending in a top, this core including a first core element to delimit a first internal cavity and a second core element of which at least one portion delimits a second internal cavity. The second cavity is situated between the first cavity and the top of the blade along the spanwise direction, and the portion of the second core element delimiting the second cavity includes a through hole, which emerges in line with an end face of the first core element to constitute a de-dusting conduit of the first cavity, this conduit traversing the second cavity from end to end while emerging in the top of the blade.

Core for the moulding of a blade having superimposed cavities and including a de-dusting hole traversing a cavity from end to end

A blade for a turbomachine bladed wheel having N blades. At one end, the blade presents a platform that is formed integrally with an airfoil of the blade. Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil. Each of these segments forms an angle of 90&#xb0;-180&#xb0;/N relative to the radial direction on either side of the airfoil.

Blade, bladed wheel, turbomachine, and a method of manufacturing the blade

A blade for a turbomachine bladed wheel, the blade comprising a root, an airfoil, and a tip. The root and the tip have respective platforms, each presenting a surface on a side toward the airfoil, which surfaces are referred to respectively as the root platform wall and the tip platform wall. Each of these platform walls is constituted by a pressure side portion and a suction side portion meeting at a crest curve.

Blade for a turbomachine impeller and method for modelling the same

A core for casting a blade of a turbomachine, the core including a first part for defining a first cavity and a second part of which at least one portion defines a second cavity located between the first cavity and the tip of the blade. The portion of the second part includes a through-hole that ends opposite the first part so as to define, in the cast blade, an outer face of a duct for removing dust from the first cavity. An alumina pin which is secured to the end face of the first part extends into the through-hole to define the inner face of the duct. A centering sheath placed between the pin and the through-hole centers the pin in relation to the through-hole. The centering sheath is made of a material that is intended to dissolve before the blade is cast around the core.

Core for casting a blade of a turbomachine

A moulding unit for producing a turbomachine blade blank. The moulding unit has an upstream portion and a downstream portion. According to the invention, the moulding unit comprises a raised portion designed to form a downstream opening which, at the level of the trailing edge, passes through at least one of the side edges of the basin-like portion at the blade tip. The raised portion rigidly secures the upstream portion to the downstream portion and comprises a strengthening protuberance extending in the transverse direction.

Unit for moulding a turbomachine blade, comprising a raised portion with a large cross-section

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 a method for producing multiple metal turbine engine parts, comprising steps consisting in:

Method for producing a turbine engine part, and resulting mould and intermediate blank

Method for producing turbine engine parts, and resulting blank and mould

Method for producing turbine engine parts, and resulting mould and blank compromising stacked parts

A method of producing cooling fluid discharge orifices in the wall of a part manufactured by the technique of lost wax casting in which a pattern of the part is produced in a wax mold, the orifices each having a first portion emerging at the external surface of the wall is disclosed. The method includes making cavities in the wax pattern that correspond to the first portions of said orifices of the part. Thus, it is possible to produce cooling air discharge orifices without sharp edges.

Method of manufacturing a turbomachine component that includes cooling air discharge orifices

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Tessancourt sur Aubette, France

Patrick Emilien Paul Emile Huchin