Abstract: A method of fabricating a composite material part includes placing a fiber texture in a mold including in its bottom portion a porous material part on which a first face of the texture rests, injecting a liquid under pressure into the fiber texture, the liquid containing a powder of refractory ceramic particles, and draining through the porous material part the liquid that has passed through the fiber texture, while retaining the powder of refractory ceramic particles inside said texture by the porous material part. A perforated rigid element is interposed between the bottom of the mold and the porous material part.

Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.

Abstract: A method of fabricating a composite material part includes placing a fiber texture in a mold including in its bottom portion a porous material part on which a first face of the texture rests, injecting a liquid under pressure into the fiber texture, the liquid containing a powder of refractory ceramic particles, and draining through the porous material part the liquid that has passed through the fiber texture, while retaining the powder of refractory ceramic particles inside said texture by the porous material part. A perforated rigid element is interposed between the bottom of the mold and the porous material part.

Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.

Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.

Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.

Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.

Abstract: A method of fabricating a part, for example a reinforcing edge for a turbomachine blade, the method including: making at least one fiber structure by three-dimensionally weaving metal yarns; and subjecting the fiber structure to hot isostatic pressing to cause the metal yarns to agglomerate so as to obtain a solid part. A composite solid part, for example a reinforcing edge for a turbomachine blade, includes a reinforcing structure of three-dimensionally woven ceramic fibers and a metal or metal alloy matrix.

Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.

Abstract: A reinforcing fiber structure woven as a single piece for fabricating a composite material part, the fiber structure having an internal portion or core (72), and a portion adjacent to an outside surface of the structure, or skin (74, 76), and the fiber structure being formed by a three-dimensional weaving in its core using at least one weave selected from an interlock weave and a multilayer weave, and by weaving at its skin with a weave of satin type that is different from the weave in the core the weaving at the skin being of the multilayer type or of the two-dimensional type.

Abstract: A method of fabricating a part, for example a reinforcing edge for a turbomachine blade, the method including: making at least one fiber structure by three-dimensionally weaving metal yarns; and subjecting the fiber structure to hot isostatic pressing to cause the metal yarns to agglomerate so as to obtain a solid part. A composite solid part, for example a reinforcing edge for a turbomachine blade, includes a reinforcing structure of three-dimensionally woven ceramic fibers and a metal or metal alloy matrix.

Abstract: A method of making a fiber structure by multilayer three-dimensional weaving, the fiber structure having a thickness in a direction perpendicular to the warp and weft directions that varies along the warp direction while conserving the same number of warp yarns that are woven at all points of the fiber structure along the warp direction, wherein during a transition in the warp direction from a first portion of the fiber texture to a second portion of the fiber texture having a thickness that is greater than the thickness of the first portion, the number of warp planes is decreased and the number of layers of warp yarns is increased without changing the number of warp yarns, by constituting at least one warp plane in the second portion with warp yarns taken from at least two different warp planes in the first portion.

Abstract: A method of making a fiber structure by multilayer three-dimensional weaving, the fiber structure having a thickness in a direction perpendicular to the warp and weft directions that varies along the warp direction while conserving the same number of warp yarns that are woven at all points of the fiber structure along the warp direction, wherein during a transition in the warp direction from a first portion of the fiber texture to a second portion of the fiber texture having a thickness that is greater than the thickness of the first portion, the number of warp planes is decreased and the number of layers of warp yarns is increased without changing the number of warp yarns, by constituting at least one warp plane in the second portion with warp yarns taken from at least two different warp planes in the first portion.

Abstract: A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimensional core weaving with at least one weave selected from interlock and multilayer weaves and by skin weaving with a weave which differs from the core weave and selected from a multilayer weave and a two-dimensional weave. It can be also formed by three-dimensional weaving with at least one core interlock weave (72) and weaving with a fabric-, satin or skin twill-type weave, wherein skin weaving is of a multilayer or two-dimensional type.

Abstract: A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the shaft, one of the bearings being capable of giving way when an unbalance occurs in the rotary assembly, at least one segment of the shaft being covered in a covering which comprises at least one piece of fabric impregnated with resin and which is for coming into contact with a surrounding portion of the turbomachine when the unbalance occurs in order to protect the first shaft and ensure that there is no risk of the first shaft rupturing. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.

Abstract: The composite turbomachine blade of the present invention comprises a preform made of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the preform. Said preform is made up of warp yarns and of weft yarns, the direction of the warp yarns forming the longitudinal direction of the preform. In characteristic manner, said preform comprises at least a first portion made using a first weave forming the airfoil of the blade, and a second portion made using a second weave forming the root of the blade, and the first and second portions are united by a transition zone in which the first weave is progressively modified to end up with the second weave, thereby obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. The invention is applicable to making a fan blade for a turbojet.

Abstract: The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a) making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b) cutting out said preform so as to leave intact a series of tracer yarns situated along a reference face of the preform; c) pre-deforming said cut-out preform; d) compacting and stiffening said pre-deformed preform; e) providing an injection mold in which said stiffened preform is placed; f) heating said injection mold; g) injecting a binder into said injection mold, the binder comprising a thermosettable resin; and h) extracting from the mold a composite molded part presenting substantially the shape and the dimensions of said blade. The invention is applicable to a making fan blade.

Abstract: A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Abstract: The invention relates to an assembly for the mounting of the foot (121) of a blade, fixed or movable, of a turbomachine, made of metal, in the aperture (101) of a support made of metal, such as a casing, a fixed flange or the disk (10) of a rotor. Characteristically, this assembly comprises, between the foot (121) and the aperture (101), a non-metallic film (20), coated or impregnated with an adhesive, in particular a fabric of glass fibres and/or polyamide fibres, advantageously comprising polytetrafluoroethylene. Application for the mounting of blades (12) of the fan on the disk (10) of the rotor, or for the fixed and/or movable blades of a compressor, in particular a low-pressure compressor.

Abstract: The invention provides a mechanical part for hinging to other mechanical parts at its ends, the mechanical part being made at least in part out of composite material from a central fiber preform and a peripheral fiber preform both of three-dimensional woven fabric, which preforms are assembled together while dry and then impregnated with resin, the peripheral preform surrounding the central preform in such a manner as to leave two empty spaces at the ends of the part and between the two preforms, which spaces are dedicated to hinging to said other parts. Metal inserts can be received in said spaces. The mechanical part can be used as a lever for a landing gear brace.