The invention relates to a setup for assembling, by brazing, a composite panel (100) comprising at least two parts separated by a filler material and intended to be joined together by brazing involving: a furnace that allows a brazing temperature for brazing the panel (100) to be achieved, an assembly device (1) comprising a form (20) having a shape similar to the final shape of the panel that is to be brazed, the setup being characterized in that the assembly device (1) further comprises, pressing means (30) designed to apply mechanical pressure to at least part of the surface of said panel (100) in a direction allowing the panel (100) to be permanently deformed into a shape the configuration of which matches that of the form (20), these pressing means (30) being designed to move under the action of elastic forcing means (210), the forces applied by said elastic forcing means (210) being determined so that, at the brazing temperature, they apply the force necessary for deforming the panel (100) against the form (20).
The invention relates to a device for absorbing vibrations between adjacent composite material blade roots of a movable turbine engine wheel, said device including a vibration-absorbing part (100) that is intended to be positioned between the side edges (24c) of the roots (24) of the two adjacent composite material blades (14) of a movable turbine engine wheel. The absorbing part includes at least two surface elements (102a to 102c) that are intended, in operation, to bear under each blade root. The device also includes an axial and radial means for supporting the absorbing part on the blade root.
According to the invention, a circular row of blades (18) is retained in the grove of a disc (15) after insertion through an axial opening that is finally blocked by a key bearing an additional blade (14). Said assembly makes it possible to provide a large number of blades on the disc (15) by suppressing the need for locking parts that separate the blades and are screwed into the groove.
Two inserts (11) are housed between the bulb (3) of the vane (4) and the wall of a groove (1) in a disk (2) to compensate for variations in slope between the overlying surfaces (6) of the groove and the upper surfaces (9) of the bulb at the central portion (12) thereof. Said construction enables the selection of vanes, the upper surfaces (9) of the bulb (3) thereof being slightly inclined with respect to the radial direction (R), which facilitates the construction thereof from a composite material.
The invention relates to a roller (100) of a continuous annealing line including at least one spindle or drive shaft (130; 140) and a cylindrical housing (120), characterised in that the cylindrical housing (120) is made of a ceramic matrix composite (CMC) material which consists of a carbon fibre reinforcement compregnated by an at least partially ceramic matrix, one phase of the ceramic material being present throughout the volume of the composite material of the housing.
The invention relates to a thermostructural composite material part including a fibrous reinforcement having fibers made of carbon or ceramic that is densified by an at least partially thin matrix α, wherein: the thickness of the part is less than 2 mm, or even less than 1 mm; the fibrous reinforcement is made of a single thickness of multilayer fabric made of spread-out threads having a count at least equal to 200 tex; the fiber volume percent is between 25% and 45%; and the ratio between the number of multilayer fabric layers and the thickness in mm of the part is at least equal to 4.
The invention relates to a supporting device (100) for loading plates or substrates in a heat treatment furnace (200), the device including a handle and a loading portion for supporting the substrates or plates inside the furnace. The device includes at least first and second structural elements (110, 120) made of a thermostructural composite material, the first element (110) forming the handle of the device, while the second element (120) forms the loading portion of said device. The first and second elements (110, 120) are mutually assembled by a removable attachment system (160). One or more individual elements (130) can also be added in order to lengthen the supporting device.
F27D 3/00 - ChargingDischargingManipulation of charge
H01L 21/677 - Apparatus specially adapted for handling semiconductor or electric solid state devices during manufacture or treatment thereofApparatus specially adapted for handling wafers during manufacture or treatment of semiconductor or electric solid state devices or components for conveying, e.g. between different work stations
The invention relates to a high-temperature annealing line roll (100) comprising a cylindrical envelope (120) and at least one spindle (130; 140) consisting of a metallic material mounted on one of the ends of the cylindrical envelope, said at least one spindle comprising a mandrel (131; 141) that can rotatably drive the cylindrical envelope (120). The cylindrical envelope (120) consists of a thermostructural composite material. The roll (100) also comprises at least one holding element (150; 160) for holding the envelope (120) on the spindle (130; 140), said element comprising a crown or a plurality of crown segments (151, 152; 161, 162) fixed to an end of said envelope, each crown or crown segment being extended by at least one elastic tongue (153; 163), the end of which is supported on the spindle.
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 (10) includes: a first phase (12) made of a material conducive to 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 (14) that are distributed within the interphase and conducive to 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.
B32B 5/22 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous
C04B 35/52 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbon, e.g. graphite
C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
The invention relates to a structuring assembly (13) for an exhaust nozzle, including the following main elements: (a) an outer skin (22) including a non-acoustic portion (33); (b) an inner structuring skin (23); (c) an acoustic structure (21) including cells (27) having a cellular core, said acoustic structure being arranged between the outer skin (22) and the inner structuring skin (23), at least one of said main elements being made of a composite material, and the acoustic structure (21) being supported between the outer skin (22) and inner structuring skin (23) by linking means (31; 41) attached to the inner structuring skin (23) and to the non-acoustic portion (33) of the outer skin (22) so as to transfer the stresses onto the inner structuring skin (23) and the non-acoustic portion (33) of the outer skin (22). The invention also relates to an exhaust nozzle for a nacelle, comprising such a structuring assembly (13), as well as to a nacelle.
The invention relates to a distributor element for a turbine, comprising an annular inner platform sector (20; 60), an annular outer platform sector (30; 70), and at least one blade (10a, 10b; 50a, 50b) extending between the platform sectors and connected thereto. The distributor element is made of a single composite material piece including a fibrous reinforcement which is densified using an at least partially ceramic matrix, wherein the fibrous reinforcement includes a fibrous woven structure produced by three-dimensional or multilayer weaving and which is continuous in the entire space of the distributor element and in the entire periphery of the blade.
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
12.
TURBINE DISTRIBUTOR ELEMENT MADE OF CMC, METHOD FOR MAKING SAME, DISTRIBUTOR AND GAS TURBINE INCLUDING SAME
The invention relates to a distributor element for a turbine, comprising an annular inner platform sector (20; 60), an annular outer platform sector (30; 70), and at least one blade (10a, 10b; 50a, 50b) extending between the platform sectors and connected thereto. The distributor element is made of a single composite material piece including a fibrous reinforcement which is densified using an at least partially ceramic matrix, wherein the fibrous reinforcement includes a fibrous woven structure produced by three-dimensional or multilayer weaving and which is continuous in the entire space of the distributor element and in the entire periphery of the blade.
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
13.
METHOD FOR PRODUCING A TURBOMACHINE BLADE MADE FROM A COMPOSITE MATERIAL
The invention relates to a method for producing a turbomachine blade from a composite material, having an integrated platform and/or shroud. The method comprises the following steps: the three-dimensional weaving of a flexible fibrous blank as a single part comprising blade vane (220) and root (230) preform portions; the separate production of a blade platform (400) or blade shroud (500) element comprising a stiffened fibrous reinforcement, whereby at least one opening in the shape of the vane profile of the blade to be produced is formed in the platform or shroud element; the mounting of the platform or shroud element, by means of the opening therein, on the flexible fibrous blank, with deformation of the latter, for assembly with the fibrous blank; the forming of the fibrous blank with the assembled platform or shroud element in order to obtain a preform (200) having a shape similar to that of the blade to be produced; the setting of the shape of the preform in a former; and the introduction of a matrix in the preform in order to obtain a blade made from a composite material and having an integrated platform or shroud.
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
14.
PROCESS FOR SMOOTHING THE SURFACE OF A PART MADE OF CMC MATERIAL.
A process for smoothing the surface of a part made from a ceramic matrix composite material having a rough and wavy surface. The process comprises depositing a refractory vitreous coating on the surface of the part (90), the vitreous coating essentially containing silica, alumina, baryte and lime.
The invention relates to a turbine ring assembly that includes a plurality of ring sectors (10) made of a single piece and of a composite material including a ceramic matrix and a ring carrier structure, each ring sector having a first portion (12) defining an annular base with an inner surface defining the inner surface of the turbine ring and an outer surface from which extend two tab portions (14, 16) having the ends thereof engaged into housings of the ring carrier structure. The ring sectors (10) have a substantially π-shaped cross section and the ends (14a, 16a) of the tabs (14, 16) are maintained without radial clearance by the ring carrier structure. Preferably, the tabs (14, 16) have at the middle section thereof a free length at least equal to three times their average width.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Plaisantin, Hervé
Pailler, René
Delcamp, Adrien
Philippe, Eric
Abstract
The invention relates to a method for processing metal carbide ceramic fibres (10), including a first reactive gaseous-phase thermal processing (S1) of the halogen type producing a superficial layer (12) mainly containing carbon by chemical conversion of the surface fibres, and a second reactive gaseous-phase thermal processing (S2) carried out with at least one second reactive gas for removing the superficial layer formed at the surface during the chemical conversion.
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
17.
ENVIRONMENTAL BARRIER FOR A REFRACTORY SUBSTRATE CONTAINING SILICON
The invention relates to a method for protecting a substrate (10), in which at least one portion adjacent to a surface is made of a refractory material containing silicon, during high-temperature use in an oxidising, humid environment, which consists of forming a boron-free environmental barrier on the surface of the substrate, having at least one layer (22) essentially made of a system of oxides formed by at least one oxide of a rare earth element, silica and alumina and which is capable of self-healing with the sustained presence of at least one solid phase in a temperature range of up to at least around 1400°C.
The invention relates to a method for smoothing a corrugated, rough surface of a part made from a ceramic matrix composite material. According to the invention, a ceramic coating is formed on the surface of the part by means of the following steps, namely: application (20) of a liquid composition on the surface of the part, said composition containing a ceramic precursor polymer and a solid refractory filler; crosslinking (40) of the polymer; and conversion (50) of the crosslinked polymer into ceramic by means of heat treatment. The method also includes the impregnation of the ceramic coating with a liquid metal composition (60).
The invention relates to a fibrous structure produced by multi-layer three-dimensional weaving with variable thickness, in a direction perpendicular to the warp (C) and weft (T) directions, in the warp direction while keeping the same number of woven warp threads at every point of the fibrous structure in the warp direction. During a transition to warp direction from a first portion of the fibrous texture to a second portion of the fibrous texture having a greater thickness than that of the first portion, the number of warp planes is reduced and the number of warp thread layers is increased without changing the number of warp threads, constituting at least one warp plane (Pl,...) in the second portion with warp threads from at least two different warp planes (Pl, P2,...) in the first portion.
The invention relates to a complexly shaped composite material part including a three-dimensional, weaved, fibrous reinforcement densified by a matrix, and manufactured through a method comprising the following steps of: - three-dimensionally weaving a continuous, fibrous strip including a series of fibrous blanks (200) made of preforms having a plurality of parts to manufacture; - then cutting individual fibrous blanks into the strip, each blank (200) being made of a single part; - shaping a cut blank to obtain a fibrous preform having a shape corresponding to that of a part to be manufactured; - setting the preform in the desired shape; and – densifying the set preform through the formation of a matrix by gaseous-phase chemical infiltration.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
The invention relates to a composite material turbine engine vane, including a fibrous reinforcement densified by a matrix, manufactured by a method that includes: - producing a fibrous blank (100) into a single part by three-dimensional weaving; - shaping the fibrous blank, whereby a fibrous preform is obtained, into a single part having a first portion, forming the preform of the vane blade and foot and at least one second portion, forming the preform of the vane platform and stub; and – densifying the preform through a matrix so as to obtain a composite material vane having a fibrous reinforcement formed through the preform, densified by the matrix, and forming a single part with a built-in platform and/or stub.
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
D03D 25/00 - Woven fabrics not otherwise provided for
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B29D 99/00 - Subject matter not provided for in other groups of this subclass
22.
METHOD FOR PRODUCING PARTS MADE OF A THERMOSTRUCTURAL COMPOSITE MATERIAL
The invention relates to a method for producing a part made of a thermostructural composite material, said method including making a fibrous preform made of wires or cables and impregnated with a consolidating composition containing a carbon or ceramic precursor, converting the precursor into carbon or ceramic by pyrolysis, and densifying the preform by gaseous-phase chemical infiltration. The consolidating composition further contains refractory solid fillers powder form having an average grain size lower than 200 nanometers and leaving, after pyrolysis, a consolidating solid phase in which the carbon or ceramic resulting from the precursor comprises a volume of between 3 and 10 % of the visible volume of the preform, while the solid fillers comprise a volume of between 0.5 and 5 % of the visible volume of the perform.
The invention relates to an afterbody assembly for an aeronautical engine including an annular part (60), made of metal material and rigidly connected to the aeronautical engine, and to an afterbody part (20), made of ceramic matrix composite material, the afterbody part (20) being mounted onto the annular part (60) by resiliently flexible mounting lugs (70) and having a first end (71) attached onto the annular part (60) and a second end (72) attached onto the upstream portion of the afterbody part (20). Each mounting lug (70) includes an axial abutment element (720) radially extending from the second end (72) of the lug and at least partially facing the first end (71). The mounting lug (70) also includes a radial abutment element (721) on the second end (72) of the lug, the radial abutment element (721) being at least partially above the first end (71).
The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).
A fibrous preform (50) is obtained by shaping panels of a fibrous texture on a former (40) having a surface that reproduces the desired geometry of a surface of the nozzle or divergent nozzle element to be produced and by linking the panels at the edges of mutual contact, and a consolidated fibrous reinforcement is produced by a forming operation carried out on the fibrous preform impregnated with a consolidating composition comprising a resin, the forming operation being carried out between the former (40) and a shell (52, 54) applied against the impregnated fibrous preform so as to obtain a consolidated fibrous reinforcement having a fibre volume fraction of at least 35% and having, over at least most of its axial dimension, a thickness of at most 5 mm. The densification of the fibrous reinforcement is continued by chemical infiltration in the gas phase after pyrolysis of the resin so that, after densification, a part is obtained having practically the shape and the wall thickness of the nozzle or divergent nozzle element to be produced.
In order to produce a self-healing layer on a part made of a composite, a composition is applied to the part, which composition contains: - a colloidal silica suspension, - boron or a boron compound in powder form, - silicon carbide in powder form, and - at least one ultra-refractory oxide.
C03C 8/14 - Glass frit mixtures having non-frit additions, e.g. opacifiers, colorants, mill additions
C03C 14/00 - Glass compositions containing a non-glass component, e.g. compositions containing fibres, filaments, whiskers, platelets, or the like, dispersed in a glass matrix
27.
A GAS TURBINE COMBUSTION CHAMBER MADE OF CMC MATERIAL AND SUBDIVIDED INTO SECTORS
An assembled annular combustion chamber comprises an annular inner wall (10) and an annular outer wall (20) made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices (30a) for receiving injectors. Elastically-deformable link parts (17, 27) connect the inner wall and the outer wall of the chamber to inner and outer casings (15, 25) 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 (110), an outer wall sector (120), and a chamber end wall sector (130). The link parts (17, 27) 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.
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
28.
A GAS TURBINE COMBUSTION CHAMBER HAVING INNER AND OUTER WALLS SUBDIVIDED INTO SECTORS
An annular combustion chamber has an inner wall (10) and an outer wall (20) of ceramic matrix composite material, together with a chamber end wall (30) that is connected to the inner and outer walls. Elastically--deformable link elements (17, 27) connect the inner wall and the outer chamber walls to inner and outer metal casings. Each of the inner and outer chamber walls (10, 20) is subdivided circumferentially into adjacent sectors (100, 200) along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outwards from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin (102, 202) that is spaced apart from the outer face of the corresponding chamber wall. The link elements (17, 27) are connected to the inner and outer chamber walls by being fastened to the sector margins.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F23R 3/60 - Support structuresAttaching or mounting means
29.
METHOD FOR MAKING A REFRACTORY CARBIDE LAYER ON A PART MADE OF C/C COMPOSITE MATERIAL
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Thebault, Jacques
Robin-Brosse, Christian
Quet, Aurélie
Pailler, René
Abstract
The invention relates to a method for making a layer of refractory carbide on the accessible surface of a C/C composite material, that comprises the step of placing the composite material in contact with a solid-form reactive composition containing an atomic proportion higher than or equal to 1/3 and lower than or equal to 95% of a predetermined carbide-precursor metal having a melting point higher than 2000°C, and an atomic proportion of silicon higher than or equal to 5% and lower than or equal to 2/3. The method further comprises the step of impregnating the accessible surface of the C/C composite material with the reactive composition molten at a temperature higher than or equal to the fusion temperature of the predetermined carbide-precursor metal.
The firing chain of the invention includes an arming device (40) mobile between a rest and an active position., two locking members (14, 16) for locking the arming device in a rest position and an active position, an arming pyrotechnical retarder (22), a squib (26) ignited at the ejection of the missile and igniting the arming retarder and releasing the first locking member (14) in order to allow the arming device to be switched into an active position, and a trajectory pyrotechnical retarder (32). A first relay charge (29) is adapted to be ignited at the end of the combustion of the arming retarder and to trigger the ignition of the trajectory retarder and the actuation of the second locking member (16) for locking the arming device in an active position and a second relay charge (34) is adapted to be ignited at the end of the combustion of the trajectory retarder and to trigger the ignition of the main charge.
F42C 15/184 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a slidable carrier
F42C 15/24 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
F42C 15/34 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by a blocking-member in the pyrotechnic or explosive train between primer and main charge
F42C 15/36 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein arming is effected by combustion or fusion of an element
The invention relates to an exhaust system (100) for directing the flow from a gas turbine, that comprises a flow directing nozzle and an exhaust casing (110) for connecting the duct nozzle to the outlet of the gas turbine. The duct nozzle includes a primary duct (120) attached to the exhaust casing (110) and a secondary nozzle (130) arranged about the primary nozzle. The exhaust system further includes a means for directly attaching the secondary nozzle (130) to the exhaust casing (110), the secondary nozzle being held by the exhaust casing independently from the primary nozzle (120).
According to the invention, in order to assemble two parts (154, 162) made of materials having different thermal expansion coefficients at their edge portions (154a, 162a) and engaged with each other, the method comprises forming along the thinned edge of one of the parts tabs (170) separated by slots (172) and obtained by cutting or machining the material of the part, and assembling the parts by attaching them (174) to the tabs. The edge portions are mutually engaged in order to be brought into mutual substantially tight contact at the high temperatures achieved during operation. The invention can particularly be used for assembling parts respectively made of a metal and a ceramic-matrix composite material, in particular in an aircraft gas turbine such as the upstream and downstream secondary nozzles.
The invention relates to a mixer (100) for the separated-flow nozzles of a turbojet, for mixing a hot inner flow from the turbojet combustion chamber with the cold outer flow from the turbojet fan. The mixer includes an inner shell (120) defining a flow channel for said hot inner flow, an outer shell (110) provided around the inner shell (120) and defining therewith a flow channel for said cold outer flow, and a lobe structure in which the lobes (1321, 1322) extend longitudinally from the trailing edges (HOa, 120a) of said shells. The lobe structure (130) is made of a ceramic-matrix composite material and is connected to the outer shell (110) by flexible connection tabs (140).
The invention relates to a packing structure intended for a fluid contacting column. The packing structure forms a volumn including an ordered arrangement of bundles of tubes having a diameter of between 5 and 50 mm. The walls of the tubes contain holes arranged so as to promote the circulation and mixing of the fluids in the structure. Said holes are disposed in rectangles having sides measuring between 2 and 45 mm and each of said holes occupies an area greater than 2 mm2.
B01J 19/32 - Packing elements in the form of grids or built-up elements for forming a unit or module inside the apparatus for mass or heat transfer
B01D 3/26 - Fractionating columns in which vapour and liquid flow pass each other, or in which the fluid is sprayed into the vapour, or in which a two-phase mixture is passed in one direction
The invention relates to a turbine ring assembly for a gas turbine, that comprises a full ring (10) made of a single piece and of a composite material having a ceramic matrix, a metal structure for holding the CMC ring including metal annular holders (20, 30) between which the CMC ring is provided while allowing for a differential expansion at least in the radial direction between the CMC ring and the annular holders, a means (40-42) for centring the CMC ring, and at least one member for rotatingly blocking the CMC ring about the axis thereof.
A turbine ring assembly for a gas turbine comprises a split ring (10) in a single piece of composite ceramic matrix material (CMC), a wedge-shaped part (20) made of CMC with the sides in contact with the ends of the ring, at both sides of the split, for closing the ring, and an annular metallic support structure (40) encircling the CMC ring and in contact with the latter over the greater part of the contour thereof, the CMC ring being fitted with preconstraint in the metallic structure, at least one element (26) exerting an elastic recoil force on the wedge-shaped part in order to keep the latter in contact with the ends of the CMC ring when the split opens under the effect of a differential dilation between the annular metallic structure and the CMC ring, and at least one element for locking for the CMC in rotation around its axis.
Method of manufacturing a gas turbine flow mixer lobed structure having an annular upstream part extended in the downstream direction by a part that forms a multi-lobed skirt, the method involving: producing a fibrous preform (100) using refractory fibres of a shape corresponding to that of the lobed structure that is to be manufactured, from several constituent elements of fibrous texture which are joined together or shaped using tooling of a shape corresponding to that of the lobed structure that is to be manufactured in order to obtain an assembled fibrous preform with a first preform part (111) corresponding to the annular part of the lobed structure and a second preform part (112) corresponding to the multi-lobed skirt of the lobed structure, the constituent elements of the fibrous preform being assembled at least partially along connecting lines (121) which run substantially in the direction in which the flow travels in the region of the lobes of the multi-lobed skirt preform part; and densifying the shaped and assembled fibrous preform using a matrix at least partially made of ceramic.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
C04B 35/00 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
38.
COMPOSITE MATERIAL PART WITH A SILICON-CONTAINING CERAMIC MATRIX PROTECTED AGAINST CORROSION
The invention relates to an environmental barrier for a substrate made of a composite material with a ceramic matrix containing silicon, essentially SiC, which is formed by an anti-corrosion protection layer containing an aluminosilicate-type compound of an alkaline or alkaline-earth or rare-earth element, e.g. BSAS, with an aluminium nitride layer being interposed as a chemical barrier between the substrate and the anti-corrosion protection layer.
The invention essentially relates to a method for producing nuclear fuel elements that comprises the steps of placing beads of nuclear fuel in a container of an ultra-porous material, applying a CVI to the container and withdrawing the container. The present invention also relates to a container for producing nuclear fuel elements comprising beads, the container being made of at least one ultra-porous material such as carbon foam.
The invention relates to a process for manufacturing a part made of a composite comprising a fibrous reinforcement densified by a matrix, which process comprises the steps of: production of a fibrous preform consolidated by impregnation (S4) of a fibrous texture comprising yarns by means of a liquid consolidation composition containing a precursor of a consolidating material and transformation (S7) by pyrolysis of the precursor made of consolidating material so as to obtain a consolidated preform of maintained shape; and densification (S8) of the consolidated fibrous preform by chemical vapour infiltration, characterized in that it includes, before the impregnation (S4) of the fibrous texture with the liquid consolidation composition, a step (S2) of filling the porosity of the yarns of said texture by means of a filling composition.
The process comprises the following steps: formation of a porous fibrous reinforcing structure; introduction of powders into the pores of the fibrous structure, said powders containing constituent elements of the matrix of the composite; and formation of at least the main part of the matrix from said powders, by reaction between the powders and/or with at least one additional element supplied; the powders introduced into the fibrous structure and the element(s) supplied comprising elements for forming at least one discontinuous healing matrix phase comprising a boron compound and at least one discontinuous matrix phase comprising a compound having a crack-deflecting lamellar structure. The formation of at least the main part of the matrix is obtained by the chemical reaction between the powders introduced into the fibrous structure and at least one additional element supplied, or by sintering the powders.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/573 - Fine ceramics obtained by reaction sintering
C04B 35/56 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
patents
