Abstract: A fibrous structure having the form of a band extending in a longitudinal direction (X) over a given length between a proximal part and a distal part and in a lateral direction (Y) over a given width between a first side edge and a second side edge, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns or strands extending longitudinally and a plurality of layers of weft yarns or strands extending laterally, wherein a first portion of the fibrous structure present between the proximal part and an intermediate part of the fibrous structure includes carbon fiber weft yarns or strands and wherein a second portion of the fibrous structure present between the intermediate part and the distal part includes glass fiber weft yarns or strands.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: A fibrous structure having the form of a band extending in a longitudinal direction (X) over a given length between a proximal part and a distal part and in a lateral direction (Y) over a given width between a first side edge and a second side edge, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns or strands extending longitudinally and a plurality of layers of weft yarns or strands extending laterally, wherein a first portion of the fibrous structure present between the proximal part and an intermediate part of the fibrous structure includes carbon fiber weft yarns or strands and wherein a second portion of the fibrous structure present between the intermediate part and the distal part includes glass fiber weft yarns or strands.

Abstract: A turbine engine blade made of composite material including fiber reinforcement obtained by weaving a first plurality of yarns with a second plurality of yarns, the yarns of the first plurality of yarns being arranged in successive layers and extending in a longitudinal direction of the fiber blank corresponding to a longitudinal direction of the blade, the reinforcement being densified by a matrix. The blade includes one or more internal channels extending in the longitudinal direction of the blade.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.

Abstract: A method designing a part made of 3D woven composite material, performed by a computer, the method including: obtaining shape data representing an outside surface of the part; for each point of a set of points of the outside surface, determining a distance between the point and a projection of the point onto a target surface, the projection being along a predetermined projection direction; determining a structure of a 3D woven preform as a function of the determined distances; and obtaining projection data specifying a projection direction as a function of a position of a point on the outside surface of the part, wherein the projection direction that is used for at least some of the points of the set of points is determined during the determining a distance, as a function of the projection and as a function of the position of the point.

Abstract: A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Abstract: A reinforcing part of ?-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix.

Abstract: A fiber structure reinforcing a composite material part woven as a single piece by multilayer weaving between plural first and second layers of yarns. The fiber structure includes a portion of decreasing thickness that presents: plural yarn withdrawal parts in surface continuity, with yarns interrupted from the first plural layers of yarns underlying the layer of yarns of the first plural layers of yarns situated in the surface of the structure; and plural yarn withdrawal parts in surface discontinuity, with yarns interrupted from the first plural layers of yarns situated at the surface of the structure, each interrupted yarn replaced in the surface of the structure by a yarn of a layer of yarns underlying the first plural layers of yarns. The yarns of the second plural layers of yarns situated in the surface of the fiber structure are continuous over at least the entire portion of decreasing thickness.

Abstract: A fiber structure for reinforcing a composite material part, the structure being woven as a single piece by multilayer weaving between a first plurality of layers of yarns extending in a first direction and a second plurality of layers of yarns extending in a second direction. The second plurality of layers of yarns includes at least one layer of variable-weight yarns, each variable-weight yarn including a separable assembly of individual yarns, each having a determined weight. The fiber structure includes at least one portion of reduced thickness in which the variable-weight yarn presents a weight that is less than the weight that it presents prior to the reduced thickness portion.

Abstract: An unducted fan of variable-pitch blades including roots engaged from outside in respective radial housings of an annular rotor element and guided to turn about their respective axes by pairs of rolling bearings, one of which is carried by an annular segment of a cylindrical skirt mounted in a groove of the annular body and by a locknut screwed onto the cylindrical skit. The bearing is covered externally by a ring including outer dog-clutch teeth co-operating with inner dog-clutch teeth of the housing to hold the ring axially in the housing. A blocking mechanism is engaged between the teeth of the housing and the teeth of the ring preventing the ring from turning and preventing the ring from being withdrawn axially from the housing.

Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.

Abstract: An aircraft propeller blade including an airfoil-profile structure. The airfoil-profile structure includes at least one fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, and a shaping part made of cellular rigid material of determined shape, the reinforcement including at least two halves linked together by continuous weaving in the leading edge of the propeller blade, the two halves fitting tightly around the shaping part.

Abstract: A fiber structure for reinforcing a composite material part, the structure being woven as a single piece by multilayer weaving between a first plurality of layers of yarns extending in a first direction and a second plurality of layers of yarns extending in a second direction. The second plurality of layers of yarns includes at least one layer of variable-weight yarns, each variable-weight yarn including a separable assembly of individual yarns, each having a determined weight. The fiber structure includes at least one portion of reduced thickness in which the variable-weight yarn presents a weight that is less than the weight that it presents prior to the reduced thickness portion.

Abstract: A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Abstract: A reinforcing part of ?-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix.

Abstract: A fiber structure reinforcing a composite material part woven as a single piece by multilayer weaving between plural first and second layers of yarns. The fiber structure includes a portion of decreasing thickness that presents: plural yarn withdrawal parts in surface continuity, with yarns interrupted from the first plural layers of yarns underlying the layer of yarns of the first plural layers of yarns situated in the surface of the structure; and plural yarn withdrawal parts in surface discontinuity, with yarns interrupted from the first plural layers of yams situated at the surface of the structure, each interrupted yarn replaced in the surface of the structure by a yarn of a layer of yarns underlying the first plural layers of yarns. The yarns of the second plural layers of yarns situated in the surface of the fiber structure are continuous over at least the entire portion of decreasing thickness.

Abstract: A method designing a part made of 3D woven composite material, performed by a computer, the method including: obtaining shape data representing an outside surface of the part; for each point of a set of points of the outside surface, determining a distance between the point and a projection of the point onto a target surface, the projection being along a predetermined projection direction; determining a structure of a 3D woven preform as a function of the determined distances; and obtaining projection data specifying a projection direction as a function of a position of a point on the outside surface of the part, wherein the projection direction that is used for at least some of the points of the set of points is determined during the determining a distance, as a function of the projection and as a function of the position of the point.

Abstract: Spacers interposed between blades attached to the disk of a rotor having slots and bottoms of the slots are disclosed. Each spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.