Abstract: A method of fabricating a textile structure of varying thickness including using a loom to weave a fiber texture in the form of a strip extending lengthwise along a longitudinal axis and widthwise along an axis perpendicular to the longitudinal axis, and causing the texture to be wound under tension onto a mandrel. The texture includes a portion presenting extra thickness. During the winding of the texture, a spacer element is interposed between adjacent turns of the fiber texture onto the mandrel. Each spacer element extends in the width direction of the texture over a portion thereof situated outside the portion of extra thickness and presenting, over the portion of the texture situated outside the portion of extra thickness, a thickness that corresponds at least to the difference between thicknesses of the portion of extra thickness and of the portion of the texture situated outside the portion of extra thickness.

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 concerns a method for manufacturing a turbomachine flow straightener made from composite material having a blade extended by at least one attachment end, comprising the operations of: forming a fibrous blank from a three-dimensional fabric comprising warp threads oriented in a direction corresponding to the longitudinal direction of the blade to be manufactured; dividing at least one end of the fibrous blank by separating in order to constitute at least two sets of integrated layers; shifting at least one set of integrated layers in a planar configuration such that the warp threads are inclined in this set of integrated layers relative to the orientation of the warp threads in the fibrous blank portion of the blade.

Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.

Abstract: A support tooling includes a mandrel presenting an outside surface onto which a fiber texture in the form of a strip is to be wound. The support tooling also has an extension including a flexible strip extending over a determined length between a first end fastened to the mandrel of the support tooling and a second end that is free and that has an attachment system suitable for holding the end of the fiber texture in the form of a strip for winding.

Abstract: A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

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 of fabricating a textile structure of varying thickness including using a loom to weave a fiber texture in the form of a strip extending lengthwise along a longitudinal axis and widthwise along an axis perpendicular to the longitudinal axis, and causing the texture to be wound under tension onto a mandrel. The texture includes a portion presenting extra thickness. During the winding of the texture, a spacer element is interposed between adjacent turns of the fiber texture onto the mandrel. Each spacer element extends in the width direction of the texture over a portion thereof situated outside the portion of extra thickness and presenting, over the portion of the texture situated outside the portion of extra thickness, a thickness that corresponds at least to the difference between thicknesses of the portion of extra thickness and of the portion of the texture situated outside the portion of extra thickness.

Abstract: A method of fabricating a textile structure of varying thickness, the method including weaving a fiber texture in the form of a strip and winding the fiber texture under tension onto a mandrel, the fiber texture including a greater-thickness portion presenting greater thickness. During winding of the fiber texture on the mandrel, an interleaving element is interposed between adjacent turns of the fiber texture on the mandrel, the interleaving element extending in the width direction of the fiber texture over a portion of the texture that lies outside the greater-thickness portion. The interleaving element presents, over the portion of the texture situated outside the greater-thickness portion, a thickness that corresponds at least to the difference between the thickness of the greater-thickness portion and the thickness of the portion of the texture situated outside the greater-thickness portion.

Abstract: A support tooling includes a mandrel presenting an outside surface onto which a fiber texture in the form of a strip is to be wound. The support tooling also has an extension including a flexible strip extending over a determined length between a first end fastened to the mandrel of the support tooling and a second end that is free and that has an attachment system suitable for holding the end of the fiber texture in the form of a strip for winding.

Abstract: A fiber preform for a hollow turbine engine vane, and a method of fabricating such a hollow vane are provided. The preform includes a first fiber structure including a main longitudinal portion for forming a pressure side wall of an airfoil; a second fiber structure including a main longitudinal portion for forming a suction side wall of the airfoil; each of the first and second fiber structures includes a first interlinking zone extending along the front edge of its main longitudinal portion, which first zones are integral with each other and form a first interlinking portion, and a second interlinking zone extending along the rear edge of its main longitudinal portion, the second zones being integral with each other and forming a second interlinking portion. The main longitudinal portions of the first and second fiber structures are dissociated so as to leave a gap between the main longitudinal portions forming an airfoil hollow.

Abstract: A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.

Abstract: The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106?) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16?) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112?; 112?) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.

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: The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106?) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16?) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112?; 112?) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.