Safran Aircraft Engines

Nicolas Ovaere

Jacques Marcel Arthur Bunel

Thomas Gricourt

Paul André Somazzi

Sylvain Zambelli

Fabien Stéphane Garnier

Pierre Jean-Baptiste Metge

Arnaud Lasantha Genilier

Mickaël Voiron

A ventilation ring for a bearing support member of an aircraft turbine engine includes two or more tubular walls and one or more spacer walls. The two or more tubular walls extend opposite each other, and one or more of the tubular walls includes a main portion and a base, the base having a thickness greater than a thickness of the main portion. The one or more spacer walls connect the two or more tubular walls. The one or more spacer walls have one or more apertures extending into the base and a rim around the aperture. An entirety of the rim has a thickness greater than a thickness of the spacer wall at a distance from the rim.

Ventilation ring for the rear bearing support member of an aircraft turbine engine

A method for producing, by additive manufacturing, a part including at least one surface that must be held during the manufacturing, the method including: a step of forming a raw part by additive manufacturing, the raw part including a support including a pillar and a head which is an alveolar element connecting the pillar to the surface to be held; and a step of detaching the support from the rest of the raw part.

Optimization of supports for the additive manufacturing of a component

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

Turbomachine output bearing support

A method for obtaining, by additive manufacture, a component including at least one recess, this method including: a step of forming, by additive manufacture, a one-piece blank component, in which the at least one recess contains a support including a core in the form of a block of material and cellular elements that connect the core to the recess; and a step of detaching the support from the rest of the blank component in order to expose the recess.

Method and apparatus for optimisation of the supports for the additive manufacturing of a component with a recess

A bearing support for an aircraft engine, manufactured, in one piece, by powder-bed additive manufacturing from a manufacturing platform, including a cylindrical element including an annular stiffener with a cross-section that changes along its circumference, this stiffener being formed with alternating portions having a &#x393;-shaped cross-section, needing to be supported during the manufacture, and portions having a Y-shaped cross-section that are not supported during the manufacture.

Growing community of inventors

Moissy-Cramayel, France

Nicolas Ovaere