Safran Aircraft Engines

Snecma

Virginie Guilbert

Thierry Georges Paul Papin

Lise Lacroix

Romain Plante

Kaelig Merwen Orieux

Thierry Francois Maurice Duchatelle

Cedric Magret

Florent Rognin

Thierry François Maurice Duchatelle

Xavier Durand

Thierry Francois Duchatelle

Thierry Georges Papin

Cédric Magret

A method of manufacturing a composite material vane with a covering element, the vane including a platform and a profile extending perpendicularly to the platform, comprises the following steps: providing a covering element and a preform of the vane, the preform comprising a platform portion and a profile portion extending substantially perpendicularly to the platform portion; positioning the covering element against the platform portion so as to obtain an assembly; placing said assembly in a mold; injecting a first resin into the mold so that said resin impregnates and covers the preform and covers at least a portion of the covering element; and carrying out a heat treatment so as to harden the first resin.

Composite material vane with integrated aerodynamic covering element and manufacturing method thereof

A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.

Turbomachine fan frame comprising improved attachment means

A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Turbine engine drive shaft device

A turbine engine casing, including a substantially cylindrical wall and a single-piece annular panel for acoustic insulation mounted radially inside the wall, is provided. The panel includes a radially outer annular surface fitted with upstream and downstream first projecting members respectively arranged in the upstream and downstream portions of the radially outer annular surface of the panel. The wall includes a radially inner annular surface fitted with upstream and downstream second projecting members that are releasably fastened respectively to the upstream and downstream first projecting members.

Turbine engine casing

Growing community of inventors

Boissise le Roi, France

Virginie Guilbert