Safran Aircraft Engines

Frédéric Jean-Bernard Pouzadoux

Matthieu Arnaud Gimat

Thomas Alain De Gaillard

Dominique Raulin

Jérémy Guivarc'h

Thibault Ruf

Gilles Pierre-Marie Notarianni

Alain Jacques Michel Bassot

Jean-Louis Romero

Jean-Michel Roux

Anthony Bernard Germain Lafitte

Alexandre Damiens

Jean-Frédéric Pierre Joseph Bruhat

The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.

Fibrous texture for turbine engine blade made of composite material

A leading-edge shield for a turbomachine blade includes a pressure-side wing and a suction-side wing. Both the pressure-side wing and suction-side wing extend heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge. They are connected together via the leading edge. The rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.

Leading edge shield

The invention provides a blade () comprising a blade body () made of organic matrix composite material reinforced by fibers and a leading edge shield () made of a material that withstands point impacts better than the composite material of the blade body. The leading edge shield () is assembled on the blade body () and the blade () includes bonding reinforcement () adhesively bonded on the leading edge shield () and on the blade body (). The invention also provides a turbojet including a fan including such blades, and also a method of fabricating such a blade.

Blade comprising a leading edge shield and method for producing the blade

A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.

A leading-edge shield () for a turbomachine blade () includes a pressure-side wing () and a suction-side wing (). Each of the wings () extends along a height (H) from a bottom edge () to a top edge () and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing () and the pressure-side wing () presents a segment (S), adjacent to the top edge () and extending over at least 10% of the height (H), wherein the rear edge () slopes towards the top edge ().

Blade, associated fan and turbojet engine

The invention relates to a blade made of composite material, provided with a reinforcement () made of a stronger material with regard to a leading edge () likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions () attached to the blade root. According to the invention, the extensions () are dissymmetric, the extension () located on the suction side being generally further back from the leading edge () than the extension () on the pressure side.

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Moissy-Cramayel, France

Frédéric Jean-Bernard Pouzadoux