Patent application number | Description | Published |
20080206048 | METHOD OF MANUFACTURING A GAS TURBINE CASING OUT OF COMPOSITE MATERIAL, AND A CASING AS OBTAINED THEREBY - A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness. | 08-28-2008 |
20130017093 | AIRCRAFT PROPELLER BLADEAANM Coupe; DominiqueAACI Le HaillanAACO FRAAGP Coupe; Dominique Le Haillan FRAANM Dambrine; Bruno Jacques GerardAACI Le Chatelet en BrieAACO FRAAGP Dambrine; Bruno Jacques Gerard Le Chatelet en Brie FRAANM Mahieu; Jean-NoelAACI ParisAACO FRAAGP Mahieu; Jean-Noel Paris FR - 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. | 01-17-2013 |
20130017094 | METHOD OF FABRICATING A COMPOSITE MATERIAL BLADE HAVING INTERNAL CHANNELS, AND A COMPOSITE MATERIAL TURBINE ENGINE BLADEAANM Coupe; DominiqueAACI Le HaillanAACO FRAAGP Coupe; Dominique Le Haillan FRAANM Dambrine; Bruno Jacques GerardAACI Le Chatelet en BrieAACO FRAAGP Dambrine; Bruno Jacques Gerard Le Chatelet en Brie FRAANM Mahieu; Jean-NoelAACI ParisAACO FRAAGP Mahieu; Jean-Noel Paris FR - 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. | 01-17-2013 |
20130105031 | METHOD FOR PRODUCING A SOLID PART | 05-02-2013 |
20130185938 | METHOD FOR MANUFACTURING A METAL PART - A method for making a metallic part, includes positioning at least one metallic coil formed from flexible metal foil including a plurality of notches, on a shaping tool, the at least one coil being manually deformable when cold along three directions in space (X, Y, Z); hot isostatic pressing the at least one metallic coil in a tool causing compaction of the metallic coil so as to obtain the metallic part. | 07-25-2013 |
20130186507 | METHOD FOR PRODUCING A FIBROUS METAL STRUCTURE BY MEANS OF WEAVING - A method for the production of a fibrous metal structure by weaving with metal weft yarns and metal warp yarns. The method includes weaving the fibrous structure by successive weaving of metal clasps that are used as weft yarns. For the purpose of weaving, each of the arms of each of the metal clasps is introduced into at least one shed, each shed being formed by two warp yarns. | 07-25-2013 |
20130219717 | METHOD FOR PRODUCING A METAL REINFORCEMENT FOR A TURBOMACHINE BLADE - A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement. | 08-29-2013 |
20130270389 | FIBROUS STRUCTURE FOR A PART MADE OF COMPOSITE MATERIAL HAVING ONE OR MORE ARCHSHAPED PORTIONS - A reinforcing fiber structure for a composite material part is woven as a single piece by multilayer weaving between plural layers of weft yarns and plural layers of warp yarns arranged in adjacent manner between two faces of the structure. The fiber structure includes at least one arcuate portion extending over one of the faces of the fiber structure, the arcuate portion including at least some of the warp yarns continuous with at least two adjacent warp yarn layers present on one of the faces of the structure. The warp yarns of the arcuate portion are of a length that is longer than the warp yarns of at least two underlying warp yarn layers of the structure. In addition, the warp yarns of the arcuate portion are not interlinked with other warp yarns of the fiber structure. | 10-17-2013 |
20130295302 | MULTILAYER WOVEN FIBROUS STRUCTURE INCLUDING A HOLLOW TUBULAR PART, PRODUCTION METHOD THEREOF AND COMPOSITE PART COMPRISING SAME - A fiber structure made as a single piece by multilayer weaving using a method including weaving warp yarns of at least a first set of layers of warp yarns with weft yarns including at least some that are woven with extra length so as to have warp yarn end portions available that extend beyond the zone of weaving, the warp yam end portions being returned to be woven with warp yarns by being reinserted in layers of warp yarns, and a hollow, or tubular, portion being formed by looping the first woven set of layers of warp yarns back onto itself and applying traction to the ends of the reinserted weft yarns so that a fiber preform for a part including a hollow portion can be obtained as a single piece. | 11-07-2013 |
20130312261 | METHOD FOR PRODUCING A REINFORCED METAL PART, SUCH AS A REINFORCEMENT FOR A TURBINE-ENGINE BLADE - A method for producing a reinforced metal part, includes: cutting out a plurality of metal foils from at least one flexible metal sheet, the foils substantially corresponding to the blank of said metal part to be produced; rigidly connecting at least one metal reinforcing wire to at least one metal foil, the metal wire being positioned depending on the orientation of the desired structural reinforcement; making a plurality of reinforced metal pockets, each metal pocket being made from two reinforced metal foils; positioning the plurality of reinforced metal pockets in shaping equipment; performing a isostatically hot-pressing of the reinforced metal pockets, causing the metal pockets and the metal reinforcing wire to be bonded together so as to produce the metal part incorporating the structural reinforcement. | 11-28-2013 |
20130319067 | METHOD FOR MANUFACTURING A METAL PART - A method for manufacturing a metal part by producing a preform with a fibrous structure of metal fibers, and subjecting the preform to hot isostatic pressing in a tool until a solid part is obtained, the tool including at least one first element including a cavity for molding the part. The first tool element is elongate in a direction between two ends, and the fibrous structure is at least partially formed by winding at least one metal wire around the first tool element in the direction, from one end to the other. The method can be used, for example, for manufacturing reinforcement parts for a fan blade of a turbojet engine. | 12-05-2013 |
20130333214 | PROCESS FOR MANUFACTURING A METAL PART, SUCH AS TURBINE ENGINE BLADE REINFORCEMENT - A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component. | 12-19-2013 |
20130333215 | PROCESS FOR MAKING A METAL PART SUCH AS A TURBINE ENGINE BLADE REINFORCEMENT - A process for manufacturing a metal part such as a metal reinforcement for the blade of a turbine engine, which includes: manufacturing a three-dimensional metal structure made up of an insert which exhibits properties which allow superplastic forming and diffusion welding to be carried out, and of multiple metal wires encircling the periphery of the insert, where the metal structure forms a preform of the metal part; positioning the metal structure in a forming tool and hot-pressing the three-dimensional metal structure which causes agglomeration of the metal structure so as to obtain the compact metal part. | 12-19-2013 |
20130333793 | FIBROUS STRUCTURE FOR A PART MADE OF A COMPOSITE MATERIAL AND HAVING A COMPLEX SHAPE - A reinforcing fiber structure woven as a single piece for fabricating a composite material part and including: first and second fiber substructures, each fiber substructure including at least one independent portion obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns that are independent from the other substructure; and an assembly portion between the least first and second fiber substructures in which a plurality of adjacent layers of warp yarns of the first fiber substructure are interlinked by at least some of the warp yarns of the second fiber substructure. | 12-19-2013 |
20130340226 | METHOD FOR MANUFACTURING AN INTEGRAL ROTATIONALLY SYMMETRICAL METAL PART INCLUDING A REINFORCEMENT CONSISTING OF CERAMIC FIBERS - A method for manufacturing an integral rotationally symmetrical part, which includes producing a blank of the part around a cylindrical mandrel, the blank including at least one fibrous structure made of composite ceramic fibers coated with metal, followed by a diffusion-welding treatment of the blank by hot isostatic pressing, and optionally machining the thus-treated blank to obtain the part. The blank includes at least a first metal-wire layer between the mandrel and the composite fibrous structure, and at least a second metal-wire layer arranged around the composite fibrous structure to cover the composite fibrous structure. | 12-26-2013 |
20130340241 | PROCESS FOR MANUFACTURING A ONE-PIECE AXISYMMETRIC METALLIC PART FROM COMPOSITE FIBROUS STRUCTURES - A process for manufacturing a one-piece axisymmetric part includes: superposition, around a rotating cylindrical mandrel of at least respectively inner and outer metal-coated composite fibrous structures, wound in first and second crossed directions on the mandrel; arranging, between the crossed inner and outer fibrous structures, at least one layer of metallic wire; then placing a blank of the part, formed by the fibrous structures and the layer of metallic wire, in a tool to apply to the blank a hot isostatic pressing treatment, and to obtain the part. | 12-26-2013 |
20140068937 | METHOD FOR FABRICATING A SINGLE-PIECE PART FOR A TURBINE ENGINE BY DIFFUSION BONDING - A method of fabricating a single-piece part for a turbine engine by diffusion bonding, the method including making a blank for the part around a mandrel, the blank including a plurality of coaxial and superposed annular layers of independent rings of metal wire that are stacked on one another around the mandrel, and subjecting the blank to hot isostatic pressing to obtain a single-piece part, and optionally machining the part. | 03-13-2014 |
20140124987 | PROCESS FOR INJECTION MOULDING A COMPOSITE PART - The invention relates to a method of injection molding a part ( | 05-08-2014 |
20140161626 | METHOD FOR MANUFACTURING AN OXIDE/OXIDE COMPOSITE MATERIAL TURBOMACHINE BLADE PROVIDED WITH INTERNAL CHANNELS - An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade. | 06-12-2014 |
20140334935 | FIBROUS REINFORCEMENT STRUCTURE FOR COMPOSITE MATERIAL PART HAVING A REDUCED THICKNESS PORTION - 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. | 11-13-2014 |
20140369847 | FIBROUS STRUCTURE HAVING VARIABLE NUMBERING YARNS - 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. | 12-18-2014 |
20140369848 | FIBER PREFORM FOR A TURBINE ENGINE BLADE MADE OF COMPOSITE MATERIAL AND HAVING AN INTEGRATED PLATFORM, AND A METHOD OF MAKING IT - 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. | 12-18-2014 |