Safran Aircraft Engines

Jeremy Guivarc'H

Dominique Raulin

Gilles Pierre-Marie Notarianni

Thibault Ruf

Frederic Jean-Bernard Pouzadoux

Francois Charleux

A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.

Blade comprising a folded leading edge shield and method of manufacturing the blade

A fitted platform for positioning between two adjacent blades of an aviation turbine engine fan includes a flow passage wall made of composite material having a central portion, and first and second margins each extending in a longitudinal direction of the wall. Each margin extends over a determined distance from the central portion in a transverse direction of the wall. The flow passage wall includes a fiber reinforcement densified by a matrix. The fiber reinforcement present in the central portion presents three-dimensional weaving, and the fiber reinforcement present in the first and second margins presents two-dimensional weaving, at least in part.

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Portsmouth, NH, United States of America

Jeremy Guivarc'H