SNECMA PROPULSION SOLIDE Patent applications |
Patent application number | Title | Published |
20140299654 | SETUP FOR ASSEMBLING A PANEL BY BRAZING - A setup for assembling, by brazing, a composite panel including at least two parts separated by a filler material and joined together by brazing. The setup includes a furnace to achieve a brazing temperature for brazing the panel, and an assembly device which has a form having a shape similar to the final shape of the panel to be brazed. In particular, the assembly device further includes a pressing device to apply mechanical pressure to at least part of the surface of the panel in a direction allowing the panel to be permanently deformed into a shape which matches that of the form. The pressing device is moved under the action of a spring, and the forces applied by the spring being determined so that, at the brazing temperature, the spring applies the force necessary for deforming the panel against the form. | 10-09-2014 |
20120308391 | LAYOUT OF A BLISK - A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material. | 12-06-2012 |
20120258641 | FIBER REINFORCING TEXTURE FOR MAKING A COMPOSITE MATERIAL PART - A fiber reinforcing texture woven as a single part for fabricating a composite material part having an inner portion, or core, made by three-dimensional weaving with yarns made up from discontinuous fibers, and a portion adjacent to an outside surface, or skin, made by weaving with yarns made up from continuous filaments. | 10-11-2012 |
20120196107 | METHOD OF FABRICATING A THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND A PART OBTAINED THEREBY - The method comprises:
| 08-02-2012 |
20120164430 | COMPOSITE MATERIAL PART HAVING A CERAMIC MATRIX, AND METHOD FOR MANUFACTURING SAME - In a composite material part having a ceramic matrix and including a fibrous reinforcement which is densified by a matrix consisting of a plurality of ceramic layers having a crack-diverting matrix interphase positioned between two adjacent ceramic matrix layers, the interphase includes a first phase made of a material capable of promoting the diversion of a crack reaching the interphase according to a first propagation mode in the transverse direction through one of the two ceramic matrix layers adjacent to the interphase, such that the propagation of the crack continues according to a second propagation mode along the interphase, and a second phase consisting of discrete contact pads that are distributed within the interphase and capable of promoting the diversion of the crack that propagates along the interphase according to the second propagation mode, such that the propagation of the crack is diverted and continues according to the first propagation mode through the other ceramic matrix layer that is adjacent to the interphase. | 06-28-2012 |
20120160933 | STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE - The invention relates to a structuring assembly ( | 06-28-2012 |
20120099982 | TURBINE DISTRIBUTOR ELEMENT MADE OF CMC, METHOD FOR MAKING SAME, DISTRIBUTOR AND GAS TURBINE INCLUDING SAME - A turbine nozzle element including an inner annular platform sector, an outer annular platform sector, and at least one vane extending between the platform sectors and connected to both of them. The nozzle element includes a single piece of composite material including fiber reinforcement densified by a matrix that is at least partially ceramic, and the fiber reinforcement includes a fiber structure that is woven by three-dimensional or multi-layer weaving, and that presents continuity throughout the volume of the nozzle element and throughout the periphery of the vane. | 04-26-2012 |
20120087795 | ROTOR FOR TURBOMACHINERY - A rotor includes a disc, on which are fixed vanes, and platforms between these vanes. The rotor is particularly remarkable in that the platforms are fixed securely and tightly to the disc. To this end, the disc includes between two successive vanes an upstream stop projecting axially from the upstream surface, and each platform includes: a plate, a retaining groove extending axially and in which the upstream stop of the disc is engaged, an axial stop bearing axially against the upstream surface of the disc. | 04-12-2012 |
20120073306 | GAS TURBINE COMBUSTION CHAMBER MADE OF CMC MATERIAL AND SUBDIVIDED INTO SECTORS - An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices for receiving injectors. Elastically-deformable link parts connect the inner wall and the outer wall of the chamber to inner and outer casings that are made of metal. The assembly formed by the inner wall, the outer wall, and the combustion chamber end wall is subdivided circumferentially into adjacent chamber sectors, each sector being made as a single piece of ceramic composite material and comprising an inner wall sector, an outer wall sector, and a chamber end wall sector. The link parts connect the inner metal casing and the outer metal casing respectively to each inner wall sector of the combustion chamber and to each outer wall sector of the chamber. The chamber end wall sectors are in contact with a one-piece ring to which they are connected. | 03-29-2012 |
20120063912 | PROCESS FOR SMOOTHING THE SURFACE OF A PART MADE OF CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite material part that presents a surface that is undulating and rough. The method includes depositing a refractory vitreous coating on the surface of the part, the vitreous coating essentially containing silica, alumina, baryte, and lime. | 03-15-2012 |
20120063904 | LEVER-ARM VIBRATION DAMPER FOR A ROTOR OF A GAS TURBINE ENGINE - A vibration damper for a rotor blade of a gas turbine engine, includes a plate for placing between an inner bearing surface and an outer bearing surface of the rotor, the bearing surfaces extending in directions that are substantially axial and being radially spaced apart from each other, the plate being folded so as to form two plate portions that are inclined relative to each other, the mass of the plate being distributed in such a manner that its center of gravity is situated on the side of one of these plate portions, the free end of the other plate portion being designed to bear radially against the inner bearing surface, and the junction zone between the two plate portions being designed to bear radially against the outer bearing surface under the effect of centrifugal force when the rotor is rotating so as to provide axial sealing against gas. | 03-15-2012 |
20120055609 | METHOD FOR PRODUCING A TURBOMACHINE BLADE MADE FROM A COMPOSITE MATERIAL - A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that comprises rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper. Additionally, final densification of the consolidated blade preform is performed in order to obtain a composite-material blade having an incorporated platform. | 03-08-2012 |
20120027605 | TURBOMACHINE BLADE, A ROTOR, A LOW PRESSURE TURBINE, AND A TURBOMACHINE FITTED WITH SUCH A BLADE - The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction. | 02-02-2012 |
20120020863 | METHOD FOR PROCESSING CERAMIC FIBERS - A method of treating ceramic fibers based on metal carbide, the method including a first reagent gas heat treatment performed with at least one first reagent gas of the halogen type that chemically transforms the surface of the fiber to obtain a surface layer constituted mainly of carbon, and a second reagent gas heat treatment performed with at least one second reagent gas that eliminates the surface layer formed during the chemical transformation. | 01-26-2012 |
20110311804 | PROCESS FOR PRODUCING A SELF-HEALING LAYER ON A PART MADE OF A C/C COMPOSITE - In order to provide a self-healing layer on a composite material part, a composition is applied to the part, the composition containing: a suspension of colloidal silica; boron or a boron compound in powder form; silicon carbide in powder form; and at least one ultra-refractory oxide. | 12-22-2011 |
20110311368 | COMPOSITE MATERIAL TURBINE ENGINE VANE, AND METHOD FOR MANUFACTURING SAME - A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, fowling a single part with incorporated inner and/or outer platform. | 12-22-2011 |
20110293828 | METHOD FOR MANUFACTURING A COMPLEXLY SHAPED COMPOSITE MATERIAL PART - A method of fabricating a complex part out of composite material including three-dimensional woven fiber reinforcement densified by a matrix, the method including three-dimensionally weaving a continuous fiber strip including a succession of fiber blanks for preforms of a plurality of parts that are to be fabricated; subsequently cutting individual fiber blanks out from the strip, each blank being a one-piece blank; shaping a cut-out blank to obtain a one-piece fiber preform having a shape that is close to the shape of a part that is to be fabricated; consolidating the preform in the desired shape; and densifying the consolidated preform by forming a matrix by chemical vapor infiltration. | 12-01-2011 |
20110277869 | PRODUCTION OF A FIBROUS STRUCTURE WITH VARIABLE THICKNESS BY 3D WEAVING - 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. | 11-17-2011 |
20110268577 | METHOD FOR SMOOTHING THE SURFACE OF A PART MADE FROM A CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite part presenting a surface that is undulating and rough. The method includes forming a ceramic coating on the surface of the part, the coating being made by applying a liquid composition on the surface of the part, the composition containing a ceramic-precursor polymer and a factory solid filler, curing the polymer, and transforming the cured polymer into ceramic by heat treatment. The method further includes impregnating the ceramic coating with a liquid metallic composition. | 11-03-2011 |
20110256411 | ENVIRONMENTAL BARRIER FOR A REFRACTORY SUBSTRATE CONTAINING SILICON - In order to protect a substrate having at least a portion adjacent to a surface that is made of a refractory material containing silicon, while the substrate is in use at high temperature in a medium that is oxidizing and wet, there is formed on the surface of the substrate an environmental barrier that contains no boron and that has at least one layer that is essentially constituted by a system of oxides formed by at least one rare earth oxide, silica, and alumina, and that is capable of self-healing by maintaining the presence of at least one solid phase in a temperature range extending up to at least 1400° C. approximately. | 10-20-2011 |
20110203255 | FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC - An after-body assembly for an aeroengine, the assembly including, in an axial direction, an annular part made of metallic material secured to the aeroengine and an after-body part made of ceramic matrix composite material presenting the form of a body of revolution at least in its upstream portion, the after-body part being mounted on the annular part by resiliently flexible fastener tabs, each fastener tab having a first end fastened to the annular part and a second end fastened to the upstream portion of the after-body part, wherein each fastener tab includes an axial abutment element extending radially from the second end of the tab, the axial abutment element facing the first end and a radial abutment element at the second end of the tab, the radial abutment element overlying the first end in a radial direction. | 08-25-2011 |
20110200748 | METHOD FOR PRODUCING PARTS MADE OF A THERMOSTRUCTURAL COMPOSITE MATERIAL - A method of fabricating a thermostructural composite material part includes making a fiber preform formed of yarns or tows and impregnated by a consolidating composition containing a carbon- or ceramic-precursor, transforming the carbon- or ceramic-precursor by pyrolysis, and then densifying the preform by chemical vapor infiltration. A consolidating composition is used that additionally contains refractory solid fillers in the powder form presenting mean grain size less than 200 nanometers and leaving, after pyrolysis, a consolidated solid phase in which the carbon or the ceramic derived from the precursor occupies a volume representing 3% to 10% of the apparent volume of the preform, and the solid fillers occupy a volume representing 0.5% to 5% of the apparent volume of the preform. | 08-18-2011 |
20110121109 | METHOD OF PRODUCING A NOZZLE OR A DIVERGENT NOZZLE ELEMENT MADE OF A COMPOSITE - A fiber preform obtained by conforming panels of fiber texture on a former having a surface that reproduces the shape desired for a surface of the nozzle or the nozzle divergent section that is to be made, and by bonding the panels together via their mutually contacting edges, and consolidated fiber reinforcement is formed by shaping the fiber preform impregnated with a consolidation composition comprising a resin, shaping being performed between the former and a jacket applied against the impregnated fiber preform so as to obtain consolidated fiber reinforcement having a fiber volume percentage of at least 35%, and having a thickness of no more than 5 mm over at least a major fraction of its axial dimension. The densification of the fiber reinforcement is continued by chemical vapor infiltration after pyrolyzing the resin so that once densified a part is obtained that has practically the shape and the wall thickness of the nozzle or the nozzle divergent section that is to be made. | 05-26-2011 |
20110108357 | ACOUSTIC PANEL FOR AN EJECTOR NOZZLE - The invention relates to an acoustic panel ( | 05-12-2011 |
20100296621 | METHOD OF MANUFACTURING NUCLEAR FUEL ELEMENTS AND A CONTAINER FOR IMPLEMENTING SUCH A METHOD - A method of manufacturing nuclear fuel elements comprising the steps of placing nuclear fuel balls in the container made from ultra-porous material, applying a CVI to the container and removing the container. The container for manufacturing fuel elements comprising balls, and is produced from at least one ultra-porous material, for example carbon foam. | 11-25-2010 |
20100144227 | REINFORCING FIBROUS STRUCTURE FOR A COMPOSITE MATERIAL AND A PART CONTAINING SAID STRUCTURE - A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core ( | 06-10-2010 |
20100126183 | CMC MIXER WITH STRUCTURAL OUTER COWLING - The invention relates to a mixer ( | 05-27-2010 |
20100111678 | TURBINE RING ASSEMBLY FOR GAS TURBINE - A turbine ring assembly for a gas turbine, the assembly comprising a complete ring ( | 05-06-2010 |
20100102144 | METHOD FOR ASSEMBLING END TO END TWO PARTS HAVING DIFFERENT THERMAL EXPANSION COEFFICIENTS AND ASSEMBLY THUS OBTAINED - In order to assembly together two parts ( | 04-29-2010 |
20100092281 | TURBINE RING ASSEMBLY FOR GAS TURBINE - A turbine ring assembly for a gas turbine comprises a one-piece split ring ( | 04-15-2010 |
20100086679 | PROCESS FOR MANUFACTURING A THERMOSTRUCTURAL COMPOSITE PART - The invention relates to a method of fabricating a composite material part comprising fiber reinforcement densified by a matrix, the method comprising the steps of:
| 04-08-2010 |
20100015428 | METHOD OF FABRICATING A THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND A PART OBTAINED THEREBY - The method comprises: | 01-21-2010 |
20100009143 | PROCESS FOR MANUFACTURING A PART MADE OF A CERAMIC MATRIX COMPOSITE CONTAINING MATRIX PHASES FOR HEALING AND DEFLECTING CRACKS - The method comprises the steps of: forming a porous fiber-reinforcing structure; introducing into the pores of the fiber structure powders containing elements for constituting the composite material matrix; and forming at least a main fraction of the matrix from said powders by causing a reaction to take place between said powders or between at least a portion of said powders and at least one delivered additional element; the powders introduced into the fiber structure and the delivered additional element(s) comprising elements that form at least one healing discontinuous matrix phase including a boron compound and at least one discontinuous matrix phase including a crack-deflecting compound of lamellar structure. At least a main fraction of the matrix is formed by chemical reaction between the powders introduced into the fiber structure and at least one delivered additional element, or by sintering the powders. | 01-14-2010 |
20100005780 | METHOD OF MANUFACTURING A CMC FLOW MIXER LOBED STRUCTURE FOR A GAS TURBINE AEROENGINE - A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising:
| 01-14-2010 |
20100003504 | COMPOSITE MATERIAL PART WITH A SILICON-CONTAINING CERAMIC MATRIX PROTECTED AGAINST CORROSION - An environmental barrier for a substrate of ceramic matrix composite material containing silicon, in particular containing SiC, is formed by an anticorrosion protection layer containing an aluminosilicate type compound of an alkali or alkaline-earth or rare earth element, e.g. BSAS, with a chemical barrier forming layer of aluminum nitride being interposed between the substrate and the anticorrosion protection layer. | 01-07-2010 |
20090280707 | FIBER REINFORCING TEXTURE FOR MAKING A COMPOSITE MATERIAL PART - A fiber reinforcing texture ( | 11-12-2009 |
20090261090 | HEAT TREATMENT OVEN WITH INDUCTIVE HEATING - The invention relates to a heat treatment oven comprising a loading or treatment zone, at least one gas inlet, a gas preheater chamber situated in the oven between the gas inlet and the loading or treatment zone, a susceptor comprising at least a side wall surrounding the preheater chamber and the loading or treatment zone, and a field winding suitable for heating the side wall by induction. The portion of the side wall of the susceptor that is situated around the preheater chamber presents at least two recesses spaced apart circumferentially from one another so as to form portions of reduced thickness in said portion of the side wall. | 10-22-2009 |
20090205952 | ELECTROLYSIS INSTALLATION - The invention relates to an electrolysis installation comprising at least two rows of electrodes that are immersed at least in part in a liquid electrolyte giving off one or more gaseous species of corrosive nature at the electrodes, at least one separation membrane being disposed between two adjacent rows of electrodes. Each membrane is constituted by carbon fiber reinforcement stiffened by a carbon matrix and presents porous portion that is permeable to ions and impermeable to the or each gaseous species, given off at the electrolytes. | 08-20-2009 |
20090186547 | REINFORCING FIBER TEXTURE WITH MULTIPLE-SATIN WEAVING FOR A COMPOSITE MATERIAL PART - A reinforcing fiber texture for a composite material part is made by multi-layer three-dimensional weaving with a satin type weave or a multiple satin type weave. The texture comprises at least three layers of weft yarns T interlaced by warp yarns C, each warp yarn taking hold in alternation of one weft yarn in n from a first layer of weft yarns and of one weft yarn in n of a second layer of weft yarns adjacent to the first, the number n being an integer not less than 3. The paths of the warp yarns are similar and they are offset in the warp direction. | 07-23-2009 |
20090169873 | Composite Material Component With Silicon-Containing Ceramic Matrix, Protected Against Corrosion - An environmental barrier is formed on a substrate ( | 07-02-2009 |
20090159437 | DEVICE FOR SUPPORTING ELECTRODES IN AN ELECTROLYSIS INSTALLATION - The invention relates to a device for supporting electrodes in an electrolysis installation, said support comprising a busbar having electrodes fastened thereto, said electrodes being disposed on either side of the busbar and extending vertically below said busbar, the busbar and said electrodes being designed to be immersed at least in part in an electrolyte that gives off one or more gaseous species of a corrosive nature. The device further comprises a protective element of carbon/carbon material placed under the busbar, the protective element being of length and width that are not less than the length and the width of the busbar. | 06-25-2009 |
20090149116 | METHOD OF FABRICATING A PART MADE UP OF A PLURALITY OF THIN-WALLED TUBES AND HAVING A SURFACE OF REVOLUTION - The invention relates to a method of fabricating a part including at least one face in the form of a surface of revolution from a structure made up of a plurality of thin-walled hollow bodies. In order to ensure that cutting takes place without damaging the walls and/or the bonds between the walls of the hollow bodies, the part is machined in the structure by means of a water jet. More precisely, during machining, the structure is attacked with a jet of water under pressure that is directed tangentially relative to the outer envelope of said at least one face to be made in the form of a surface of revolution. | 06-11-2009 |
20090120743 | METHOD OF SILICIDING THERMOSTRUCTURAL COMPOSITE MATERIALS, AND PARTS OBTAINED BY THE METHOD - Within the pores of a porous thermostructural composite material, there is form an aerogel or xerogel made up of a precursor for a refractory material, the precursor is transformed by pyrolysis to obtain an aerogel or xerogel of refractory material, and then it is silicided by being impregnated with a molten silicon type phase. The aerogel or xerogel is formed by impregnating the composite material with a composition containing at least one organic, organometalloid, or organometallic compound in solution, followed by in situ gelling. The method is applicable to improving the tribological properties or the thermal conductivity of C/C or C/SiC composite material parts, or to making such parts leakproof. | 05-14-2009 |
20090110877 | Method and substrate for making composite material parts by chemical vapour infiltration densification and resulting parts - A composite material part is made by forming a fiber preform ( | 04-30-2009 |
20090098331 | METHOD OF PRODUCING A FIBROUS LAYER FOR THE MANUFACTURE OF A PREFORM OF A COMPOSITE PART - The invention provides a method of making a fiber ply for forming a preform of a composite part in the form of a body of revolution having a non-developable surface, the method being characterized in that it comprises the steps consisting in: | 04-16-2009 |
20090036283 | ROLLER OF THERMOSTRUCTURAL COMPOSITE MATERIAL - The invention relates to a roller comprising an axial support element made of metal and comprising at least two shafts, and a cylindrical shell made of thermostructural composite material. In order to compensate for differential expansion between the metal axial support element and the cylindrical shell made of thermostructural composite material, radial clearance is provided with the axial support element and the cylindrical shell. | 02-05-2009 |
20080311301 | Protection Against the Oxidation of Composite Materials Containing Carbon - A part made of a porous material containing carbon, in particular a C/C composite material, is protected against oxidation by being impregnated with a composition in an aqueous medium containing at least a phosphorous compound, elemental titanium, and boron or a boron compound other than titanium diboride, to form in the presence of oxygen and at least one alkali or alkaline-earth element M that catalyses oxidation of carbon, at least one P—O—Ti-M type association bonded by boron oxide B | 12-18-2008 |