Safran Aircraft Engines

Snecma

Safran

Marc Soisson

Valéry Piaton

Serge Alain Fargeas

Sébastien Digard Brou De Cuissart

Patrick Emilien Paul Emile Huchin

Anthony Texier

Karine Deschandol

Alexandre Gimel

Amar Saboundji

Ba-Phuc Tang

Sebastien Digard Brou De Cuissart

Guillaume Martin

Saïd Boukerma

Maxime Paul Numa Givert

Josserand Jacques André Bassery

Gabriela Mihaila

Janusz Lisowski

Valery Piaton

Said Boukerma

The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness Xwhich cannot be directly obtained by step a).

Method for producing a metal bladed element for a turbomachine of an aircraft

A rough cast blading of this blade includes, a suction sidewall and/or a pressure sidewall of this blading intended to respectively form the suction sidewall and/or the pressure sidewall of the blade, a casting allowance extending over a determined width from a trailing edge of the blading intended to form the trailing edge of the blade in the direction of a leading edge of the blading intended to form the leading edge of the blade, except for a reserved area adjacent to the trailing edge of the blading and whose width is at least one radius of the trailing edge of the blading, over at least part of the height of the blading.

Rough cast blading with modified trailing edge geometry

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

The invention concerns a unit comprising a mold () adapted to receive a molten metal alloy and the said metal alloy poured therein. The alloy is TiAl. The mold is rotational and comprises receiving recesses () made of steel, metal alloy and/or ceramic, and, at the location of a plurality of section planes each passing through the mold and the poured metal alloy, the mold has a surface heat capacity less than that of the poured metal alloy.

Lined centrifugal mould with controlled thermal inertia

The invention relates to a rotary mold for centrifugal casting of an alloy. The mold comprises liners () housed in hollow exoskeletons (). The exoskeletons retain the liners against the centrifugal force, during the casting, while the mold is spinning.

Lined mold for centrifugal casting

Growing community of inventors

Moissy-Cramayel, France

Marc Soisson