A method of fabricating a composite material part, the method including making a consolidated fiber preform, the fibers of the preform being carbon or ceramic fibers and being coated with an interphase; obtaining a consolidated and partially densified fiber preform, the partial densification comprising using chemical vapor infiltration to form a first matrix phase on the interphase; and continuing densification of the fiber preform by infiltrating an infiltration composition containing at least silicon and at least one other element suitable for lowering the melting temperature of the infiltration composition to a temperature less than or equal to 1150° C.
C23C 16/00 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes
C23C 16/22 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the deposition of inorganic material, other than metallic material
The present invention relates to a device (1) for dispensing a material, said device (1) comprising a body (2) that defines a storage chamber (4) in which the material to be dispensed is present, and a pressurizing chamber (5) comprising a gas generator (20), the pressurizing chamber (5) being separated from the storage chamber (4) by a movable wall (7) that has at least one fragile portion (7a), the storage chamber (4) being delimited by an end wall (2b) of the body that has at least one outlet opening (10) and at least one relief (12), the gas generator (20) being configured to trigger the dispensing of the material out of the body (2) through the outlet orifice (10) by causing the device (1) to pass from a first configuration for storing the material to a second configuration for the end of dispensing of the material, the movable wall (7) being set in movement towards the end wall (2b) in order to break the fragile portion (7a) by impact with the relief during the passage from the first configuration to the second configuration.
A62C 13/22 - Portable extinguishers which are permanently pressurised or pressurised immediately before use with pressure gas produced by chemicals with incendiary substances producing pressure gas
A62C 35/02 - Permanently-installed equipment with containers for delivering the extinguishing substance
B65D 83/34 - Cleaning or preventing clogging of the discharge passage
A62C 13/02 - Portable extinguishers which are permanently pressurised or pressurised immediately before use with pressure gas produced by chemicals
B05B 9/08 - Apparatus to be carried on or by a person, e.g. of knapsack type
B05B 15/02 - Arrangements or devices for cleaning discharge openings
B65D 83/64 - Contents and propellant separated by piston
A62C 3/07 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
3.
CVI densification installation including a high capacity preheating zone
A thermochemical treatment installation includes a reaction chamber, at least one gas inlet, and a gas preheater chamber situated between the gas inlet and the reaction chamber. The preheater chamber has a plurality of perforated distribution trays held spaced apart one above another. The preheater chamber also includes, between at least the facing distribution trays, a plurality of walls defining flow paths for a gas stream between said trays.
C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for heating the substrate
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
F28C 3/00 - Other direct-contact heat-exchange apparatus
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
B01J 8/02 - Chemical or physical processes in general, conducted in the presence of fluids and solid particles; Apparatus for such processes with stationary particles, e.g. in fixed beds
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
C23C 16/452 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for generating reactive gas streams, e.g. by evaporation or sublimation of precursor materials by activating reactive gas streams before introduction into the reaction chamber, e.g. by ionization or by addition of reactive species
F27B 5/16 - Arrangements of air or gas supply devices
F27D 7/06 - Forming or maintaining special atmospheres or vacuum within heating chambers
C23C 16/04 - Coating on selected surface areas, e.g. using masks
F27D 99/00 - Subject matter not provided for in other groups of this subclass
F28F 3/08 - Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
4.
TREATMENT OF EFFLUENT FROM HYDROLYSIS OF CHLORINATED GASES.
The present invention relates to a continuous method for treating gases containing metal chlorides resulting from a ceramic process. The invention is characterized in that it includes the following successive steps: a) hydrolysis of the gas containing metal chlorides resulting from a ceramic process by placing said gas in contact with softened water having a pH ≥ 7, more particularly between 7 and 11, such that a hydrochloric acid solution is produced; b) treatment of the hydrochloric acid solution obtained in step a) by passing same over a weak anion-exchange resin such that the Cl- ions are exchanged for OH- ions and such that an aqueous solution having a pH > 7, more particularly between 7 and 11, is obtained; c) use of the treated solution obtained at step b) in step a).
A thermostructural composite material part including carbon or ceramic fiber reinforcement densified by a matrix having at least one thin portion in which: the thickness of the part is less than 2 mm, or indeed less than 1 mm; the fiber reinforcement is made as a single thickness of multilayer fabric made of spread yarns having a weight of not less than 200 tex; the fiber volume ratio lies in the range 25% to 45%; and the ratio between the number of layers of the multilayer fabric and the thickness in millimeters of the part is not less than four.
C04B 35/52 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing 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 composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
The present invention relates mainly to substantially cylindrical gas-generating pyrotechnical monolithic blocks, characterised by having: a thickness no lower than 10 mm, an equivalent diameter no lower than 10 mm, and a porosity lower than 5%; and a composition, given as weight percentages, which contains, for at least 94% of the weight thereof: + 77.5% to 92.5% of guanidine nitrate, + 5% to 10% of basic copper nitrate, and + 2.5% to 12.5% of at least one inorganic titanate with a melting temperature higher than 2100 K. Said blocks are particularly efficient, in particular as regards their combustion temperature and speed (low), the ease with which they can be obtained, and their gas yield.
A process for manufacturing a multiperforated composite part comprises the following steps: - positioning a sandblasting mask (250) on a preform (110) comprising a fibrous texture impregnated with a polymerized ceramic precursor resin, said mask comprising a plurality of openings (251) corresponding to the perforations to be made in the preform (110), - spraying abrasive particles at high speed onto the surface of the mask (250) so as to perforate the preform (110) exposed in the openings of said mask, - pyrolysis of the multiperforated perform so as to form a ceramic matrix in the multiperforated fibrous texture.
B28B 1/00 - Producing shaped articles from the material
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
A process for manufacturing a multiperforated composite part comprises the following steps: - positioning a sandblasting mask (250) on a preform (110) comprising a fibrous texture impregnated with a polymerized ceramic precursor resin, said mask comprising a plurality of openings (251) corresponding to the perforations to be made in the preform (110), - spraying abrasive particles at high speed onto the surface of the mask (250) so as to perforate the preform (110) exposed in the openings of said mask, - pyrolysis of the multiperforated perform so as to form a ceramic matrix in the multiperforated fibrous texture.
B28B 1/48 - Producing shaped articles from the material by removing material from solid section preforms for forming hollow articles, e.g. by punching or boring
B28B 11/08 - Apparatus or processes for treating or working the shaped articles for reshaping the surface, e.g. smoothing, roughening, corrugating, making screw-threads
A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.
F42B 10/66 - Steering by varying intensity or direction of thrust
F42B 15/01 - Arrangements thereon for guidance or control
F42B 10/40 - Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
F42B 10/00 - Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
F42B 15/00 - Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
10.
CVI DENSIFICATION EQUIPMENT INCLUDING A HIGH-CAPABILITY PREHEATING AREA
The invention relates to thermochemical treatment equipment (100) which includes: a reaction chamber (140); at least one gas inlet (104); and a gas preheating chamber (110) located between the gas inlet (104) and the reaction chamber (140). The preheating chamber (110) includes a plurality of perforated distribution plates (111-114) that are kept spaced apart, above one another. The preheating chamber (110) also includes, between at least the distribution plates facing one another, a plurality of walls (1110, 1120, 1130) defining gas flow paths between said plates (111-114).
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C04B 35/00 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C23C 16/452 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for generating reactive gas streams, e.g. by evaporation or sublimation of precursor materials by activating reactive gas streams before introduction into the reaction chamber, e.g. by ionization or by addition of reactive species
F27B 5/16 - Arrangements of air or gas supply devices
F27D 7/06 - Forming or maintaining special atmospheres or vacuum within heating chambers
F27D 99/00 - Subject matter not provided for in other groups of this subclass
F28F 3/08 - Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
11.
METHOD FOR TREATING WASTE GAS CONTAINING POLYCYCLIC AROMATIC HYDROCARBONS
The present invention relates to a method for treating waste gas containing polycyclic aromatic hydrocarbons, comprising a stage of washing by spraying mineral oil in order to trap said hydrocarbons, characterized in that the mineral oil comprises a mixture of aromatic mineral oil and naphthenic mineral oil. The method further comprises the use of a naphthenic mineral oil to reduce the viscosity of an aromatic mineral oil loaded with polycyclic aromatic hydrocarbons, advantageously with an aromatic mineral oil containing at most 30% by volume polycyclic aromatic hydrocarbons.
A section (100) of a turbine stator comprising a plurality of blades (110) made from a composite material and each comprising a blade body (111) extending between first and second ends (112, 113). The section further comprises first and second platforms (120, 130) made from composite material, the first platform (120) comprising openings (121) in which the first ends (112) of the blades (110) are engaged and the second platform (130) comprising openings (131) in which the second ends (113) of the blades (110) are engaged. The openings (121) of the first platform (120) have dimensions larger than the dimensions of the first ends (112) of the blades (110) engaged in said openings (121), in such a way as to provide clearance (J) between the first end (112) of each blade (110) and the opening (121). Each first blade end (112) engaged in the opening (121) has dimensions smaller than the dimensions of the blade body (111) in such a way as to define a shoulder (1121) extending around said first end (112). The shoulder has dimensions larger than the dimensions of the openings (121) of the first platform (120).
The present invention relates to a method for treating waste gas containing polycyclic aromatic hydrocarbons, comprising a stage of washing by spraying mineral oil in order to trap said hydrocarbons, characterized in that the mineral oil comprises a mixture of aromatic mineral oil and naphthenic mineral oil. The method further comprises the use of a naphthenic mineral oil to reduce the viscosity of an aromatic mineral oil loaded with polycyclic aromatic hydrocarbons, advantageously with an aromatic mineral oil containing at most 30% by volume polycyclic aromatic hydrocarbons.
B01D 53/14 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by absorption
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating
14.
STATOR SECTION FOR A TURBOMACHINE AND METHOD FOR PRODUCING THE SAME
A section (100) of a turbine stator comprising a plurality of blades (110) made from a composite material and each comprising a blade body (111) extending between first and second ends (112, 113). The section further comprises first and second platforms (120, 130) made from composite material, the first platform (120) comprising openings (121) in which the first ends (112) of the blades (110) are engaged and the second platform (130) comprising openings (131) in which the second ends (113) of the blades (110) are engaged. The openings (121) of the first platform (120) have dimensions larger than the dimensions of the first ends (112) of the blades (110) engaged in said openings (121), in such a way as to provide clearance (J) between the first end (112) of each blade (110) and the opening (121). Each first blade end (112) engaged in the opening (121) has dimensions smaller than the dimensions of the blade body (111) in such a way as to define a shoulder (1121) extending around said first end (112). The shoulder has dimensions larger than the dimensions of the openings (121) of the first platform (120).
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
The invention relates to : • a sized yarn (1) intended to undergo a textile operation comprising: • - a plurality of ceramic and/or carbon fibres (2), • - an interphase coating (3, 3') that covers the fibres, and • - a film (4) that covers the interphase coating comprising a linear-chain polysiloxane.
The invention relates to : a sized yarn (1) intended to undergo a textile operation comprising: - a plurality of ceramic and/or carbon fibres (2), - an interphase coating (3, 3') that covers the fibres, and - a film (4) that covers the interphase coating comprising a linear-chain polysiloxane.
A part (300) made from an oxide/oxide composite material comprising a fibrous reinforcement (310) consisting of a plurality of layers of warp threads (312) and of weft threads (311) linked together by three-dimensional weaving, the spaces between the reinforcing threads being filled by a matrix of refractory oxide (320). The part is characterized in that the fibrous reinforcement has a fabric weave selected from one of the following weaves: interlock, multi-layer, multi-satin and multi-twill, and a thread count in the warp and weft of between 4 and 20 threads/cm. The fibrous reinforcement further has a volume density of fibres of between 40% and 51%.
A part (300) made from an oxide/oxide composite material comprising a fibrous reinforcement (310) consisting of a plurality of layers of warp threads (312) and of weft threads (311) linked together by three-dimensional weaving, the spaces between the reinforcing threads being filled by a matrix of refractory oxide (320). The part is characterized in that the fibrous reinforcement has a fabric weave selected from one of the following weaves: interlock, multi-layer, multi-satin and multi-twill, and a thread count in the warp and weft of between 4 and 20 threads/cm. The fibrous reinforcement further has a volume density of fibres of between 40% and 51%.
A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method.
The invention relates to a composite composition for solid propellant comprising a) an energy charge, b) a possible reducing charge, c) an energetic binder comprising an energetic plasticiser based on nitric esters and a stabiliser of the nitric esters, and d) a cross-linking system, characterised in that the stabiliser of the nitric esters is selected from the epoxidised fatty acid esters.
C06B 23/00 - Compositions characterised by non-explosive or non-thermic constituents
C06B 45/10 - Compositions or products which are defined by structure or arrangement of component or product comprising solid particles dispersed in solid solution or matrix the solid solution or matrix containing an organic component the organic component containing a resin
21.
COMPOSITE PYROTECHNICAL PRODUCT WITH NON-CROSSLINKED BINDER AND METHOD FOR PREPARING SAME
The present invention relates to composite pyrotechnical products, in particular to propellant powders for barrelled weapons, in which the composition, expressed in weight percentages, includes: 78 % to 90 %, advantageously 80 % to 86 %, of organic energy loads; and 10 % to 22 % of a polymer gum, selected among the polyurethane-polyester gums, the polyurethane-polyether gums and the mixtures thereof, in which the average molecular weight by number is higher than 20,000 g/mol and in which the Mooney viscosity is from 20 to 70 ML (5 + 4) at 100 °C. The invention also relates to the method for obtaining said products. Said products are particularly useful given the properties thereof and how easily they can be obtained.
C06B 45/10 - Compositions or products which are defined by structure or arrangement of component or product comprising solid particles dispersed in solid solution or matrix the solid solution or matrix containing an organic component the organic component containing a resin
C06B 21/00 - Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
22.
COMPOSITE PYROTECHNICAL PRODUCT WITH CROSSLINKED BINDER AND METHOD FOR PREPARING SAME
The present invention relates to a composite pyrotechnical product, in particular a propellant powder for barrelled weapons, containing organic energy loads in a crosslinked binder. The composition of said product, expressed in weight percentages, typically includes: 78 % to 90 %, advantageously 80 % to 86 %, of organic energy loads; and 10 % to 22 % of an energetic crosslinked binder obtained by crosslinking, via only 8 % to 12 % of the azide functions thereof, a glycidyl polyazide having an average molecular weight of 700 to 3,000 g/mol, with at least one crosslinking agent containing at least two propargyl functions in the chemical formula thereof, in the presence of a polymer gum, selected among the polyurethane-polyester gums, the polyurethane-polyether gums and the mixtures thereof, in which the average molecular weight by number is higher than 20,000 g/mol and in which the Mooney viscosity is from 20 to 70 ML (5 + 4) at 100 °C; said at least one polymer gum making up 1 wt % to 5 wt % of the composition of said pyrotechnical product. The invention also relates to the method for obtaining said products. Said products are particularly useful given the properties thereof and how easily they can be obtained.
C06B 21/00 - Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
C06B 45/10 - Compositions or products which are defined by structure or arrangement of component or product comprising solid particles dispersed in solid solution or matrix the solid solution or matrix containing an organic component the organic component containing a resin
23.
POLYMERS WITH AZIDE END FUNCTIONS, PRODUCTION THEREOF, SOLID PROPELLANTS OBTAINED FROM SAID POLYMERS
The subject matter of the present invention is: polymers with azide end functions of formula (V): - the production of such polymers + from a hydroxytelechelic polymer of formula (I): OH-P-OH, + from an azido alcohol of formula (II): HO-R1N3, and + from a diisocyanate of formula (III): O=C=N-R2-N=C=O; - the solid propellants which can be obtained from said polymers. Said propellants are capable of containing energetic fillers of any type, in particular energetic fillers with intrinsic acidity.
C08F 136/14 - Homopolymers of compounds having one or more unsaturated aliphatic radicals, at least one having two or more carbon-to-carbon double bonds the radical having only two carbon-to-carbon double bonds conjugated containing elements other than carbon and hydrogen
C08F 8/30 - Introducing nitrogen atoms or nitrogen-containing groups
C08G 65/333 - Polymers modified by chemical after-treatment with organic compounds containing nitrogen
C08G 63/685 - Polyesters containing atoms other than carbon, hydrogen, and oxygen containing nitrogen
C08G 63/91 - Polymers modified by chemical after-treatment
C08J 3/24 - Crosslinking, e.g. vulcanising, of macromolecules
C06B 23/00 - Compositions characterised by non-explosive or non-thermic constituents
24.
METHOD AND DEVICE FOR INERTING AN AIRCRAFT FUEL TANK
The present invention relates to a method for inerting a tank (S) of fuel (6) of a moving aircraft and to a related device (1a, 1b, 1c). Said method includes dispensing an inerting gas into said tank (5) while the volume (V) of fuel (6) in said tank (5) decreases as a result of the engine(s) of said aircraft consuming the fuel. Said method characteristically includes: keeping at least one tank (2) pressurized using an inerting gas consisting of at least 90% nitrogen in volume, generated by combusting and/or decomposing separate solid loads (8), at least some of said loads (8) being, for the purpose of keeping said tank under pressure, ignited differently and independently from one another in the patent application; and continuously supplying pressurized inerting gas from said at least one tank (2) into the free space (v) of said tank (5) of fuel (6) in expansion, such as to inert said free space (v). The pressure inside said tank (2) is monitored while said supplying of inerting gas is carried out.
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
A62D 1/06 - Fire-extinguishing compositions; Use of chemical substances in extinguishing fires containing gas-producing, chemically-reactive components
B01J 19/14 - Production of inert gas mixtures; Use of inert gases in general
B65D 90/44 - Means for reducing the vapour space or for reducing the formation of vapour within containers by use of inert gas for filling space above liquid or between contents
C06D 5/06 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
25.
METHOD FOR CONNECTING A SKIRT TO AN ENGINE BODY CASING
The invention relates to a method for connecting the end portion of a prefabricated skirt (22) to an engine body casing (10) near a base thereof, wherein said method includes: moving the end portion (22b) of the skirt (22) into a position with circumferential clearance around the engine body casing (10) near the base (14); keeping the skirt in position relative to the engine body casing; closing both ends of an annular space (46) between the end portion (22b) of the skirt (22) and the engine body casing (10); injecting an elastomer into said annular space (46); and cross-linking the elastomer.
An industrial facility (500) for chemical vapour infiltration of porous substrates comprising a sealed reaction chamber (110), a supply circuit (400), a discharge circuit (200) connected to the reaction chamber (110) and a heat exchanger (210). The facility further comprises: - an accelerated cooling circuit (300) comprising at least one inlet (301a) in selective communication with the outlet of the heat exchanger (210), and an outlet (301b) in selective communication with the supply circuit (400), - first connection means (2110; 2030) for connecting the discharge circuit (200) to the inlet of the heat exchanger (210), - second connection means (3010) for directly or indirectly connecting the inlet (301a) of the accelerated cooling circuit (300) to the outlet of the heat exchanger (210) when the reaction chamber (110) is supplied with said at least one cooling gas.
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for heating the substrate
27.
Method of fabricating a composite material part with improved intra-yarn densification
A method of fabricating a composite material part comprises fiber reinforcement densified by a matrix. The method comprises the following steps: making a fiber fabric by weaving yarns having an initial mean fiber percentage; and densifying the fiber fabric with a matrix. The fiber fabric is subjected, prior to densification, to one or more jets of water under pressure so as to reduce the mean fiber percentage in the fabric to a value lying in the range 20% to 45%.
System (20) for the emergency starting of aircraft turbomachines, comprising at least one solid-fuel gas generator (22), an electrically operated ignition device (24), a computer (28) connected to the ignition device, and at least two independent starters (18) each one intended to start a turbomachine, each starter comprising a turbine (38) for driving a shaft (34) intended to be coupled to a shaft (54) of the corresponding turbomachine, the gas outlet of the generator being connected to the inlet (44) of the turbine of each starter by one and the same distribution valve (26) connected to the computer (28).
The invention relates to a process for fabricating a composite part, comprising the steps of: - producing a consolidated fibrous preform, the fibres of the preform being carbon fibres or ceramic fibres and being coated with an interphase, - obtaining a consolidated and partially densified fibrous preform, the partial densification comprising the formation, on the interphase, on a first matrix phase obtained by chemical vapour infiltration, and - continuation of the densification by infiltration of the fibrous preform with an infiltration composition containing at least silicon and at least one other element capable of lowering the melting point of the infiltration composition to a temperature less than or equal to 1150°C.
A space vehicle (1), in particular a satellite or a probe, capable of executing high-thrust maneuvers or high specific impulse maneuvers. According to the invention, the space vehicle (1) includes at least one solid-propellant chemical thruster (10-14) and at least one electric thruster (20-24).
The present invention concerns a composite solid propellant of which the composition contains an oxidising charge and a reducing charge in a binder. The reducing charge characteristically consists of particles of at least one aluminium/magnesium alloy or consists of a mixture of particles of at least one aluminium/magnesium alloy and aluminium particles; said reducing charge containing a total quantity of magnesium that represents less than 3 %, and advantageously less than 1 %, of the mass of same. The presence of such a low level of magnesium helps reduce the thrust instabilities of a rocket engine operating with said propellant and helps increase the propulsive performances of said rocket engine.
C06B 33/06 - Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
C06B 45/10 - Compositions or products which are defined by structure or arrangement of component or product comprising solid particles dispersed in solid solution or matrix the solid solution or matrix containing an organic component the organic component containing a resin
32.
METHOD FOR DELIVERING A LIQUID PRESSURISED BY THE COMBUSTION GASES FROM AT LEAST ONE PYROTECHNIC CHARGE
The present invention mainly concerns a method for delivering a liquid (L) contained in a tank (1), said tank (1) having at least one port (2) for delivering said liquid (L) sealed by a seal (3) that can be retracted when a threshold pressure is applied to said liquid (L), comprising: the combustion of at least one pyrotechnic charge (7) in order to generate combustion gases, the pressurisation of said liquid (L) under the action of said combustion gases, and the retraction of said retractable seal (3) from said at least one delivery port (2) and the delivery of said pressurised liquid (L), characterised in that the flow of generated combustion gases during the delivery of said liquid (L) provides almost constant pressurisation of said liquid (L) and therefore the delivery of said liquid (L) at an almost constant flow rate; the pressure of said liquid (L) during the delivery of said liquid varying by a maximum of only +/- 30 %, advantageously by a maximum of only +/- 20 %, and very advantageously by a maximum of only +/- 10 %, relative to the initial of same at the time when said seal or seals (3) is/are retracted; and in that it is implemented in a device (100; 101; 102) comprising said tank (1) and at least one pyrotechnic gas generator (15; 16; 17) containing said at least one pyrotechnic charge (7; 7'; 70; 700; 700'); said at least one pyrotechnic gas generator (15; 16; 17) being connected to said tank (1) and a movable member (4) for separating the generated combustion gases and said liquid (L) being provided inside said device (100; 101; 102).
A62C 13/22 - Portable extinguishers which are permanently pressurised or pressurised immediately before use with pressure gas produced by chemicals with incendiary substances producing pressure gas
A62C 35/02 - Permanently-installed equipment with containers for delivering the extinguishing substance
A62C 35/08 - Containers destroyed or opened by bursting charge
33.
ASSEMBLY HAVING A TEMPERATURE-DEPENDENT SELF-TIGHTENING CONNECTION
The invention relates to an assembly (100) comprising a first part (10) and a second part (20) made of composite material that are held against one another by at least one fastening system (50) comprising a rivet (30) that has a countersunk head (31) from which there extends a shank (32) that has a widened end (320) and a washer (40) that engages with the widened end (320) of the shank (32) of the rivet (30). The head (31) of the rivet (30) bears against a countersunk hole (12) made in the first part (10), the washer (40) bearing against the second part (20). The washer (40) has, on its face (43) opposite the one (42) bearing against the second part (20), a portion (430) with a conical shape. The washer (40) also has a central countersunk hole (410) on the surface of which the widened end (320) of the shank (32) of the rivet (30) rests.
A part comprising a substrate (10), at least one portion of which adjacent to a surface of the substrate is made of a refractory material containing silicon, is protected by an environmental barrier (20) formed on the surface of the substrate and having at least one self-healing layer (22) containing a rare-earth silicate. At least 90 mol% of the self-healing layer (22) is formed from a system consisting of 30 mol% to at most 80 mol% of at least one rare-earth silicate RE2Si2O7, RE being a rare earth, and at least 20 mol% to 70 mol% of manganese oxide MnO; and at most 10 mol% of the self-healing layer (22) is formed from one or more oxides, except MnO, having a eutectic point with SiO2 lower than or equal to 1595°C, the self-healing layer (22) exhibiting a liquid phase having a self-healing function in at least the entire temperature range extending from 1200°C to 1400°C while preserving a predominantly solid phase.
A part comprising a substrate (10), at least one portion of which adjacent to a surface of the substrate is made of a refractory material containing silicon, is protected by an environmental barrier (20) formed on the surface of the substrate and having at least one self-healing layer (22) containing a rare-earth silicate. At least 90 mol% of the self-healing layer (22) is formed from a system consisting of 30 mol% to at most 80 mol% of at least one rare-earth silicate RE2Si2O7, RE being a rare earth, and at least 20 mol% to 70 mol% of manganese oxide MnO; and at most 10 mol% of the self-healing layer (22) is formed from one or more oxides, except MnO, having a eutectic point with SiO2 lower than or equal to 1595°C, the self-healing layer (22) exhibiting a liquid phase having a self-healing function in at least the entire temperature range extending from 1200°C to 1400°C while preserving a predominantly solid phase.
A pyrotechnic charge (1) for a pyrotechnic gas generator comprises a plurality of blocks (12) of pyrotechnic material stacked in layers (10), each block (12) being delimited by two main faces substantially orthogonal to the direction (A) of the stack. In this pyrotechnic charge (1), each layer (10) of the stack comprises at least two distinct blocks (12) of pyrotechnic material each one forming an angular sector of an annulus or of a disc, said blocks being assembled to form an annulus (14) and/or a disc.
F42B 3/04 - Blasting cartridges, i.e. case and explosive for producing gas under pressure
F02K 9/18 - Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
F42B 5/16 - Cartridges, i.e. cases with propellant charge and missile characterised by composition or physical dimensions or form of propellant charge or powder
F42B 30/12 - Mortar projectiles with provision for additional propulsive charges; with provision for varying the length
37.
ASSEMBLY HAVING A TEMPERATURE SELF-LOCKING CONNECTION
An assembly (100) comprising a first part (10) and a second part (20) made from a composite material held together by at least one fixing system (50) comprising a screw (30) comprising a countersunk head (31) from which a threaded portion (32) extends and a nut (40) comprising a countersunk head (41) from which a barrel (42) extends comprising a tapped hole (43) that engages with the threaded portion (32) of the screw (30). The head (31) of the screw (30) bears against a recess (12) provided in the first part (10). The head of the nut (41) engages in a recess (22) provided in the second part (20). The fixing system (50) is capable of making each head (31, 41) tilt towards the recess (12; 22) in which it is housed when the fixing system (50) expands axially.
A rotor disc blade (10) for a turbomachine made from composite material comprising a fibrous reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade (10) comprises a portion that forms the airfoil (12) and the blade root (14) forming a single part, the blade root (14) having two substantially planar opposing side flanks (22, 24) that are formed in the respective extensions of the pressure (12a) and suction (12b) surfaces of the airfoil (10). The blade root (14) is gripped between two metal plates (26, 28) fixed against the side flanks (22, 24) of the blade root by a screw (30) and a nut (40) passing through the plates (26, 28) and the blade root (14). The screw (30) comprises a head (31) bearing on one (26) of the two plates. The nut (40) comprises a head (41) bearing on the other plate (28). The screw and the nut (30, 40) apply, to the metal plates (26, 28), a minimum clamping force capable of taking up, by friction between the metal plates (26, 28) and the side flanks (22, 24) of the blade root (14), a predefined centrifugal force applied to the blade (10).
An assembly (100) comprising a first part (10) and a second part (20) made from a composite material held together by at least one fixing system (50) comprising a screw (30) comprising a countersunk head (31) from which a threaded portion (32) extends and a nut (40) comprising a countersunk head (41) from which a barrel (42) extends comprising a tapped hole (43) that engages with the threaded portion (32) of the screw (30). The head (31) of the screw (30) bears against a recess (12) provided in the first part (10). The head of the nut (41) engages in a recess (22) provided in the second part (20). The fixing system (50) is capable of making each head (31, 41) tilt towards the recess (12; 22) in which it is housed when the fixing system (50) expands axially.
A rotor disc blade (10) for a turbomachine made from composite material comprising a fibrous reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade (10) comprises a portion that forms the airfoil (12) and the blade root (14) forming a single part, the blade root (14) having two substantially planar opposing side flanks (22, 24) that are formed in the respective extensions of the pressure (12a) and suction (12b) surfaces of the airfoil (10). The blade root (14) is gripped between two metal plates (26, 28) fixed against the side flanks (22, 24) of the blade root by a screw (30) and a nut (40) passing through the plates (26, 28) and the blade root (14). The screw (30) comprises a head (31) bearing on one (26) of the two plates. The nut (40) comprises a head (41) bearing on the other plate (28). The screw and the nut (30, 40) apply, to the metal plates (26, 28), a minimum clamping force capable of taking up, by friction between the metal plates (26, 28) and the side flanks (22, 24) of the blade root (14), a predefined centrifugal force applied to the blade (10).
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Blanchard, Hélène
Renouard, Joël, A.
Darwiche, Ali
Janot, Raphaël, L.
Abstract
The invention concerns: a method of obtaining a solid form containing heat-stable borazane, said solid form being capable of generating hydrogen by thermal decomposition or by a self-sustained combustion reaction, the solid form containing heat-stable borazane; and a hydrogen-generating method comprising the thermal decomposition or self-sustained combustion of the solid form containing heat-stable borazane. According to the invention, within said borazane-containing solid form, the borazane is stabilized thermally as a result of an oxidized layer being formed on the surface thereof.
C01B 3/04 - Production of hydrogen or of gaseous mixtures containing hydrogen by decomposition of inorganic compounds, e.g. ammonia
C06D 5/06 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
C06B 45/30 - Compositions or products which are defined by structure or arrangement of component or product comprising a coated component the component base containing an inorganic explosive or an inorganic thermic component
C06D 5/04 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by auto-decomposition of single substances
The invention relates to a pyrotechnical gas generator (10) for actuating a cylinder (100), including a body defining a combustion chamber (12) which contains a main pyrotechnical load (14), and an igniter (16, 18) for initiating the combustion of said main pyrotechnical load (14). The pyrotechnical gas generator (10) includes at least one retarding chamber (22) suitable for communicating with the combustion chamber (12) via at least one inlet (62), and the retarding chamber (22) is provided with at least one outlet (63) for the passage of the gases outside the gas generator, wherein said outlet is provided with a seal (73) suitable for moving from a closed state to an open state when the pressure inside the retarding chamber reaches a maximum breaking pressure (P1).
A holding tool (100) for holding a porous rotating preform comprises a lower ring (110) and an upper ring (120) held coaxially above the lower ring by at least one spacer member (130). Each ring (110; 120) comprises, on the outer surface of same, a bearing (111; 121) intended to be in contact with a part of a porous preform (10). At least one (110) of the two rings (110, 120) comprises a cylindrical bearing, the outer surface of each ring (110; 120) being further coated with a compressible material (112, 122) capable of creating sliding contact with the part of the porous preform with which it is in contact.
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
44.
METHOD FOR PRODUCING A COMPOSITE MATERIAL WITH A CARBIDE MATRIX
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Jacques, Sylvain
Ledain, Olivier
Maille, Laurence
Delcamp, Adrien
Piquero, Thierry
Abstract
A method for densifying a porous substrate (50) by means of a matrix, said method comprising the steps of: - fractionation of the porosity present in the porous substrate in such a way as to form, in said substrate, a microporosity network, said fractionation being carried out with a filling composition comprising at least one carbon phase or one carbide phase accessible via the microporosity network, - reactive gaseous-phase chemical infiltration of the microporosity network formed by the filling material, said infiltration being carried out with a reactive gaseous composition free of carbon and comprising at least one element capable of reacting with the carbon of the filling composition in order to form a carbide (53).
C04B 35/56 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
C04B 35/573 - Fine ceramics obtained by reaction sintering
C04B 35/563 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on boron carbide
45.
METHOD FOR OBTAINING SOLUTIONS OF OTA IN A CONCENTRATED SULPHURIC ACID MEDIUM; SAID SOLUTIONS; AND METHOD FOR PREPARING ONTA
The present invention relates to a method for obtaining solutions that contain 1,2,4-triazole-5-one (3) (OTA) in concentrated sulphuric acid, said method using 3-amino-1,2,4-triazole (1) (ATA) as a precursor of OTA (3); to said solutions and to a method for preparing 3-nitro-1,2,4-triazole-5-one (4) (ONTA) from said solutions.
A device for modulating a gas ejection section (100) comprising a partial sealing member (111) for partially sealing a nozzle neck (13), a control guide (112) for controlling the sealing member (111), a main piston (120) and a priming piston (130). The control guide (112) is movable between a retracted position in which the partial sealing member (111) is retracted relative to the nozzle neck (13) and a sealing position in which the partial sealing member (111) is in contact with the nozzle neck (13). The priming piston (130) is movable between an idle position and a priming position of the main piston (120) when the pressure in the modulation device reaches a first predefined value. The main piston (120) is movable between a first locked position that locks the movement of the control guide (112) in the retracted position of same and a second locked position that locks the control guide (112) when the pressure in the modulation device reaches a second predefined value lower than the first predefined value.
F02K 9/86 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross-section
47.
NOZZLE HAVING A VARIABLE NECK SECTION FOR A SPACECRAFT THRUSTER PROVIDED WITH A MOBILE NEEDLE
A nozzle having a variable neck section for a spacecraft thruster, comprising a cylindrical housing having a neck (30) of which the opening diameter is smaller than the diameter of the housing, and a needle (24) capable of sliding into the housing between a front position of high-flow operation in which a nose (28) is recessed relative to the neck of the housing and a back position of low-flow operation in which the nose is abutted against the neck, the needle comprising a rod (26) intended to slide into the housing in the nozzle, the rod ending with the nose having a decreasing diameter. The nose of the rod is capable of coming into abutment against the neck of the housing in the nozzle forming a seat, and comprises at least two axial grooves (34) provided on the outer periphery of same to allow gas to flow when the nose axially abuts against the neck of the housing in the nozzle.
F02K 9/86 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross-section
F02K 1/08 - Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
F02K 9/80 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
The present invention concerns a method (and the associated device) for supplying a fuel cell (3) with a hydrogenated gas (G), consisting essentially of hydrogen, at a pressure lower than or equal to 5.105 Pa and at a temperature lower than 250°C, and generally lower than 200°C. Said method comprises: a) burning at least one hydrogenated-gas generating solid pyrotechnic charge (7) in order to produce a hot, pressurised hydrogenated gas (GO) containing at least 70 mol% hydrogen; b) supplying and operating an open-cycle two-reservoir heat engine (2) with at least one portion of said hot, pressurised hydrogenated gas (GO) containing at least 70 mol% hydrogen, that has been produced; said heat engine (2) then delivering an expanded and cooled hydrogenated gas (Gl) corresponding to said at least one portion of this hydrogenated gas (GO) that has been produced; c) supplying said fuel cell (3) with a hydrogenated gas (G) corresponding to at least one portion of said hydrogenated gas (Gl) delivered by said heat engine (2), expanded to a pressure lower than or equal to 5.105 Pa and cooled to a temperature lower than 250°C, and generally lower than 200°C. Said method has a particularly advantageous energy balance.
C06D 5/06 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
C01B 3/06 - Production of hydrogen or of gaseous mixtures containing hydrogen by reaction of inorganic compounds containing electro-positively bound hydrogen, e.g. water, acids, bases, ammonia, with inorganic reducing agents
49.
SPACE PROPULSION MODULE HAVING ELECTRIC AND SOLID-FUEL CHEMICAL PROPULSION
A space propulsion module in particular for equipping spacecraft such as satellites, probes, or indeed upper stages of rockets. According to the invention, this space propulsion module comprises a solid-fuel chemical thruster (10), having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid-fuel chemical thruster (10).
The invention relates to a nozzle with a movable divergent, comprising a fixed throat (210) forming a spherical joint and a divergent (220) with an upper part that is movably mounted around the throat (210). An annular lubrication chamber (230) is arranged between the throat (210) and the upper part of the divergent (220), the chamber comprising a grease seal (231). The nozzle also comprises: an annular lamination element (310) arranged between the throat (210) and the divergent (220), downstream from the lubrication chamber (230), said lamination element consisting of a refractory material; and an annular thermal protection element (320) arranged between the throat (210) and the divergent (220), upstream from the lamination element (310), said thermal protection element (320) closing the lubrication chamber (230) in the lower part (230b) thereof.
F02K 1/00 - Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
F02K 9/84 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
51.
Assembly formed by a turbine nozzle or a compressor diffuser made of CMC for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly
A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of sectors, each presenting upstream and downstream attachment tabs. Each inner platform presents on the inside an upstream hook and a downstream hook, and the abradable material support ring is supported by the nozzle or the diffuser by mutually engaging without fastening together firstly the end portions of the upstream attachment tabs and the upstream hooks and secondly the end portions of the downstream attachment tabs and the downstream hooks.
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
52.
PROCEDE DE FABRICATION D'UNE STRUCTURE ALVEOLAIRE DE FORME COURBEE EN MATERIAU COMPOSITE
The invention relates to a method for producing a curved honeycomb structure, comprising the following steps: producing a deployable fibrous structure (100) by means of the multi-layer weaving of a plurality of layers of warp yarns and a plurality of layers of weft yarns, said fibrous structure comprising separating zones which extend through the thickness of the fibrous structure and are spaced from one another by linking portions between multiple layers of weft yarns, the linking portions being offset by one or more weft yarns in a direction parallel to that of the layers of weft yarns between each series of weave planes; impregnating the fibrous structure (100) with a precursor resin of a pre-determined material; deploying the fibrous structure (100) on a holding tool (50) such as to form, in the fibrous structure, a cell or honeycomb in each separating zone, said tool also having a curved shape corresponding to the shape of the honeycomb structure to be produced; polymerising the resin of the fibrous structure such as to form a curved honeycomb structure comprising a plurality of cells or honeycombs.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
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
D03D 25/00 - Woven fabrics not otherwise provided for
53.
METHOD FOR THE PRODUCTION OF A CURVED CERAMIC SOUND ATTENUATION PANEL
The invention relates to a method for producing a curved sound attenuation panel, comprising the following steps: impregnating a fibrous structure defining a honeycomb structure (150) with a ceramic precursor resin; polymerising the ceramic precursor resin while maintaining the fibrous structure on a tool having a curved shape corresponding to the end shape of the honeycomb structure (150); applying first and second skins to the honeycomb structure (150), each skin being formed by a fibrous structure (200; 300) impregnated with a ceramic precursor resin and each skin being applied to the honeycomb structure before or after polymerisation of the resin of the skins; pyrolysing the assembly formed by the honeycomb structure and the first and second skins; and densifying the assembly by means of gas-phase chemical infiltration.
C04B 35/48 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on zirconium or hafnium oxides or zirconates or hafnates
C04B 35/571 - Fine ceramics obtained from polymer precursors
C04B 35/573 - Fine ceramics obtained by reaction sintering
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
The invention relates to a method for producing a curved honeycomb structure, comprising the following steps: producing a deployable fibrous structure (100) by means of the multi-layer weaving of a plurality of layers of warp yarns and a plurality of layers of weft yarns, said fibrous structure comprising separating zones which extend through the thickness of the fibrous structure and are spaced from one another by linking portions between multiple layers of weft yarns, the linking portions being offset by one or more weft yarns in a direction parallel to that of the layers of weft yarns between each series of weave planes; impregnating the fibrous structure (100) with a precursor resin of a pre-determined material; deploying the fibrous structure (100) on a holding tool (50) such as to form, in the fibrous structure, a cell or honeycomb in each separating zone, said tool also having a curved shape corresponding to the shape of the honeycomb structure to be produced; polymerising the resin of the fibrous structure such as to form a curved honeycomb structure comprising a plurality of cells or honeycombs.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
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
D03D 25/00 - Woven fabrics not otherwise provided for
55.
METHOD FOR THE PRODUCTION OF A CURVED CERAMIC SOUND ATTENUATION PANEL
The invention relates to a method for producing a curved sound attenuation panel, comprising the following steps: impregnating a fibrous structure defining a honeycomb structure (150) with a ceramic precursor resin; polymerising the ceramic precursor resin while maintaining the fibrous structure on a tool having a curved shape corresponding to the end shape of the honeycomb structure (150); applying first and second skins to the honeycomb structure (150), each skin being formed by a fibrous structure (200; 300) impregnated with a ceramic precursor resin and each skin being applied to the honeycomb structure before or after polymerisation of the resin of the skins; pyrolysing the assembly formed by the honeycomb structure and the first and second skins; and densifying the assembly by means of gas-phase chemical infiltration.
C04B 35/571 - Fine ceramics obtained from polymer precursors
C04B 35/573 - Fine ceramics obtained by reaction sintering
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
C04B 35/48 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on zirconium or hafnium oxides or zirconates or hafnates
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Reglero, José
Loison, Sylvie
Aymonier, Cyril
Huguet, Chrystel
Evrard, Hervé
Abstract
The present invention relates to a method of treating silicon carbide fibres comprising the step of chemically treating the fibres with water under homogeneous subcritical conditions or in the vicinity of the critical point at a pressure between the saturation vapour pressure and 30 MPa and at a temperature less than or equal to 400°C in order to selectively eliminate the silicon present at the surface of the fibres and to form a microporous carbon layer. It also relates to a method of fabricating a fibrous preform comprising the formation of a fibrous structure based on treated silicon carbide fibres and the use of this preform for fabricating a composite material part.
The invention relates to a lightning protection device (200) intended to be fitted to a structure (100) that is to be protected, and comprising: a first coating comprising at least one coat of conducting paint (202), a second coating (204) placed on the surface coating and containing a thermally insulating and electrically conducting material.
The invention relates to a cross-linkable elastomer composition comprising a mixture (a) of an elastomer composition based on an ethylene-propylene-diene terpolymer elastomer and (b) between 2 and 14 wt. %, in relation to the total weight of the composition, of an amphiphilic statistical copolymer or a block copolymer of a saturated or unsaturated hydrocarbonated C2-C4 polymer functionalised by a polar functional group comprising a maleic anhydride group. The invention also relates to the cross-linked composition, to the method for the preparation thereof, and to the use of same as thermal protection and/or internal sealing of a composite material and/or for accommodating the mechanical deformations of said composite material. The invention further relates to an assembly comprising (A) a structure consisting of a composite material and (B) a coating layer consisting of a cross-linked elastomer composition according to the present invention, to the production method thereof and to the use of same in the fields of aeronautics or aerospace.
C08L 23/16 - Ethene-propene or ethene-propene-diene copolymers
C08L 51/06 - Compositions of graft polymers in which the grafted component is obtained by reactions only involving carbon-to-carbon unsaturated bonds; Compositions of derivatives of such polymers grafted on to homopolymers or copolymers of aliphatic hydrocarbons containing only one carbon-to-carbon double bond
C08L 51/04 - Compositions of graft polymers in which the grafted component is obtained by reactions only involving carbon-to-carbon unsaturated bonds; Compositions of derivatives of such polymers grafted on to rubbers
59.
PYROTECHNIC PROCESS FOR PROVIDING VERY HIGHLY PURE HYDROGEN AND ASSOCIATED DEVICE
The subject matter of the present invention is a pyrotechnic process for providing very highly pure hydrogen (G) and also a device (100) suitable for implementing said process. Said process comprises: the combustion of at least one solid pyrotechnic charge which generates hydrogen-containing gas (4a, 4b, 4c, 4d) for the production of a hot hydrogen-containing gas (G1) under pressure, containing at least 70% by volume of hydrogen; and the purification of at least one part of said hydrogen-containing gas (G1) under pressure, by passage through a metallic membrane for separating the hydrogen (9) maintained at a temperature above 250°C, advantageously between 300 and 600°C, so as to obtain, at the outlet of said membrane (9), a hydrogen-containing gas (G) containing at least 99.99% by volume of hydrogen.
C01B 3/06 - Production of hydrogen or of gaseous mixtures containing hydrogen by reaction of inorganic compounds containing electro-positively bound hydrogen, e.g. water, acids, bases, ammonia, with inorganic reducing agents
C06B 47/10 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing free boron, an organic borane or a binary compound of boron, except with oxygen
60.
PYROTECHNIC PROCESS FOR PROVIDING VERY HIGHLY PURE HYDROGEN AND ASSOCIATED DEVICE
The subject matter of the present invention is a pyrotechnic process for providing very highly pure hydrogen (G) and also a device (20) suitable for implementing said process. Said process comprises: - the combustion of at least one solid pyrotechnic charge which generates hydrogen-containing gas (2) for the production of a hot hydrogen-containing gas (Gl) under pressure, containing at least 70% by volume of hydrogen; - the cooling of at least one part of said hot hydrogen-containing gas (Gl) under pressure, which is produced, then the expansion of said at least one part of said cooled hydrogen-containing gas (G2); and - the purification of said at least one part of said cooled and expanded hydrogen-containing gas (G3) by passage through a zeolite adsorbent filter (11) so as to obtain, at the outlet of said filter (11), a hydrogen-containing gas (G) containing at least 99.99% by volume of hydrogen.
C01B 3/06 - Production of hydrogen or of gaseous mixtures containing hydrogen by reaction of inorganic compounds containing electro-positively bound hydrogen, e.g. water, acids, bases, ammonia, with inorganic reducing agents
61.
Turbine engine stator wheel and a turbine or a compressor including such a stator wheel
A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.
Device for kneading a paste allowing a paste to be kneaded and extruded reliably and in a stabilized manner notably for the manufacture of explosives, and offering greater ease of maintenance. According to the invention, this paste-kneading device comprises an oblong barrel (10), two shafts (14a, 14b) running parallel to one another within the barrel (10), held and driven at their first ends (15a, 15b) defining the upstream end (AM) by a drive device (12), two screws (20a, 20b) each formed of flights borne by the shafts (14a, 14b), each screw (20a, 20b) comprising at least one transport section (21a‑21d) bearing a main flight (21') for progressing the paste along the two screws (20a, 20b), and an outlet orifice (19) made in the wall of the barrel (10) to discharge the kneaded paste; the kneading device further comprises a retaining device (30) configured to hold each shaft (14a, 14b) at its second end (16a, 16b), defining the downstream end (AV), and allowing it to rotate freely, this retaining device (30) comprising, for each shaft (14a, 14b), a first part (31) secured to said shaft (14a, 14b) and a second part (36) secured to an end cap part (13) of the barrel (10), this end cap part (13) being removable and said first (31) and second (36) parts being configured to engage and disengage freely.
The present invention relates mainly to a method for synthesising hexanitrohexaazaisowurtzitane. Said method includes the following two steps, carried out in sequence: hexa-N-deallylation of 2,4,6,8,10,12-hexaallyl-2,4,6,8,10,12-hexaazatetracyclo(5.5.0.05'9.03,11)dodecane or hexaallylisowurtzitane (HallylIW), in order to obtain stabilised hexaazaisowurtzitane (HAIW); and nitration of said stabilised hexaazaisowurtzitane (HAIW).
C07D 487/22 - Heterocyclic compounds containing nitrogen atoms as the only ring hetero atoms in the condensed system, not provided for by groups in which the condensed system contains four or more hetero rings
C06B 25/34 - Compositions containing a nitrated organic compound the compound being a nitrated acyclic, alicyclic or heterocyclic amine
The invention relates to a combined steering and drag-reduction device intended for a missile comprising a base (13) and an upper part which are arranged in succession along a main axis (11) along which the missile is steered. Advantageously, the device comprises a pressurized-gas generator (35) and at least one lateral thruster (20) comprising: - at least one nozzle (38a, 38b), configured to deliver thrust, by expansion of the gas transmitted by the generator (35), which nozzle can be orientated about an axis substantially perpendicular to the main axis (11), - at least one stabilizing chamber (39), configured to expand the gas transmitted by the generator (35) and expel it through an exit section (43) of the base (13) substantially perpendicular to the main axis (11).
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
HERAKLES (France)
Inventor
Roux, Guilhem
Chaumat, Valérie
Conete, Eric
Abstract
The present application describes a brazing method for assembling a first part (10) and a second part (20) made from silicon carbide material, the first and second parts (10, 20) each comprising an assembly portion (11; 21) intended to be brazed with the assembly portion (21; 11) of the other part. The method comprises clamping together the assembly portions (11, 21) of the first and second parts (10, 20), interposing a brazing composition (41) between the assembly portions or close to said assembly portions, and brazing the assembly portions. The method further comprises a step of forming a plurality of ports (110, 210) in the assembly portions (11, 21) of the first and second parts. The ports are formed at predefined positions so as to align the ports (110) of the assembly portion (11) of the first part (10) with the ports (210) of the assembly portion (21) of the second parts (20) during the clamping step. An element (31) of a clamping member (30) is inserted through each pair of opposing ports (110, 210), each clamping member (30) applying a clamping force between the assembly portions (11, 21).
A method for locally treating a portion (130) of a part (100) made from composite material comprising a fibrous reinforcement densified by a matrix, said material having internal porosity. The method comprises the following steps: - defining a quantity of infiltration composition (10) on the basis of the volume of the portion (130) of the part to be treated (100), the infiltration composition (10) comprising at least silicon, - placing the defined quantity of infiltration composition (10) in contact with the portion (130) of the part to be treated, - heat treating at a temperature greater than or equal to the melting temperature of the infiltration composition in such a way as to impregnate said portion with the treatment composition.
A method for producing an aerodynamic part comprising: - producing a preform (300) from a composite material made of a fibrous structure densified by a matrix, said preform having dimensions smaller than those of the aerodynamic part to be produced, - placing the preform made from composite material into a mould (400) having the same internal dimensions and shape as those of the aerodynamic part to be produced, - interposing a ceramic powder (50) between the preform made from composite material and the internal surface (402a) of the mould, said ceramic powder having a thermal expansion coefficient varying, at most, by 4.10"6.K_1 relative to the thermal expansion coefficient of the composite material of the preform, said ceramic powder further having a particle size of between 0.25 µm and 25 µm, - stabilising said powder in such a way as to form, around the preform made from composite material, a ceramic shell having the dimensions and the shape of the aerodynamic part to be produced.
The invention relates to a vane (10) for a turbine engine, made of a composite material including a fiber reinforcement obtained by means of three-dimensional weaving of threads and densified by a matrix. The vane includes a blade (12) and a vane base (14) that form a single part, the vane base having two substantially planar, opposite side flanks closed between two separate composite material plates (24) that are attached onto the side flanks of the vane base such as to form a bulb-shaped vane base.
The part made of a matrix composite at least mainly made of ceramic is manufactured by a method comprising: producing a fibrous preform from silicon carbide fibres containing less than 1 at% oxygen; depositing on the fibres of the preform a boron nitride interphase, the deposit being carried out by gaseous phase chemical infiltration with a deposition rate lower than 0.3 um/h; carrying out a heat treatment for stabilising the boron nitride of the interphase, after deposition of the interphase, without prior exposure of the latter to an oxidising atmosphere before depositing a matrix layer on the interphase, the heat treatment being carried out at a temperature above 1300°C and at least equal to the maximum temperature subsequently encountered until densification of the preform by the matrix is complete; and next, densification of the preform by a matrix at least mainly made of ceramic.
The invention relates to a method for manufacturing a casing (10), made of a composite material, for a gas-turbine engine, the method including the production of an outer hoop (100) including a flange (104) and a flat (106), the production of an inner hoop (200) having a smaller diameter than the outer hoop and including a flange (202) and a flat, the production of a plurality of casing arms (300) each including a blade (302) ending in a flange at each radial end, the arrangement in the respective flange of the hoops of a plurality of openings each intended for receiving a flange of a casing arm, and the assembly of the arms of the casing on the outer hoop and on the inner hoop by inserting the flanges of the casing arms in the openings in the hoops. The invention also relates to a casing made of a composite material obtained by such a method.
A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
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
C04B 35/571 - Fine ceramics obtained from polymer precursors
Chemical vapour infiltration apparatus (600) for infiltrating three-dimensional porous preforms (20) mainly extending in a longitudinal direction, the apparatus comprising: a parallelepipedal reaction chamber (610), the side walls (612, 613) of the reaction chamber comprising heating means (615); and a plurality of stacks (50) of loading devices (10) placed in the reaction chamber (610), each loading device (10) being formed from a parallelepipedal recipient equipped with supporting elements intended to receive the porous preforms (20) to be infiltrated.
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for heating the substrate
73.
METHOD FOR BRAZING PARTS MADE FROM A COMPOSITE MATERIAL, WITH ANCHORING OF THE BRAZED JOINT
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
Inventor
Revel, Thomas
Conete, Eric
Philippe, Eric
Chaumat, Valérie
Abstract
The invention relates to a method for the braze-assembly of two parts (10, 20) made from a composite material, each part comprising an assembly face (10a, 20a) intended to be brazed to the assembly face of the other part. The method comprises the following steps: producing a plurality of cavities (101) in the assembly face (10a) of at least one of the two parts (10) made from composite material, at least one portion of said cavities opening onto one or more portions (10b, 10c) of the part that do not form part of the assembly face; inserting capillary elements (30) between the assembly faces of the parts made from composite material; placing a brazing composition (41) in contact with one portion of the capillary elements (30); liquefying the brazing composition (41) by means of heat treatment, such as to produce the capillary distribution of the molten brazing composition between the assembly faces (10a) of the parts of composite material.
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
Inventor
Revel, Thomas
Conete, Eric
Philippe, Eric
Roux, Guilhem
Bucci, Philippe
Abstract
The invention relates to a method for the braze-assembly of a first part (10) and a second part (20) made from a composite material, said first and second parts (10, 20) each comprising an assembly face (10a, 20a) intended to be brazed to the assembly face of the other part. The method comprises the following steps: producing at least one perforation (101) in the assembly face of the first part (10); inserting capillary elements (30) between the assembly faces (10a, 20a) of the first and second parts (10, 20) made from composite material; positioning the first and second parts (10, 20) facing one another, with the insertion of a slug (5) in each perforation in the first part (10); placing a brazing composition (41) in contact with part of the capillary elements (30); liquefying the brazing composition (41) by means of heat treatment, such as to produce the capillary distribution of the molten brazing composition between the assembly faces of the first and second parts of composite material.
Chemical vapour infiltration apparatus (600) for infiltrating three-dimensional porous preforms (20) mainly extending in a longitudinal direction, the apparatus comprising: a parallelepipedal reaction chamber (610), the side walls (612, 613) of the reaction chamber comprising heating means (615); and a plurality of stacks (50) of loading devices (10) placed in the reaction chamber (610), each loading device (10) being formed from a parallelepipedal recipient equipped with supporting elements intended to receive the porous preforms (20) to be infiltrated.
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for heating the substrate
C23C 16/04 - Coating on selected surface areas, e.g. using masks
The present invention relates to a method for supplying a missile engine with a storable propellant, which includes the consecutive steps of: 1) generating combustion gas by combustion of a pyrotechnic charge, and pressurising said storable propellant by means of said combustion gas; and then 2) selectively supplying said pressurised storable propellant to said engine. In a characteristic manner, said method is implemented with a pyrotechnic charge which generates combustion gases essentially made up of hydrogen.
C01B 3/06 - Production of hydrogen or of gaseous mixtures containing hydrogen by reaction of inorganic compounds containing electro-positively bound hydrogen, e.g. water, acids, bases, ammonia, with inorganic reducing agents
C06B 47/10 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing free boron, an organic borane or a binary compound of boron, except with oxygen
F02K 9/50 - Feeding propellants using pressurised fluid to pressurize the propellants
77.
ACTIVATED-STROKE ACTUATOR PROVIDED WITH DAMPED RETURN TRAVEL
The invention relates to an actuated-stroke actuator having at least one additional pyrotechnic charge in order to adapt the anti-return resistance according to a desired development. According to the invention, at least one additional pyrotechnic charge (21a-21c) is placed in a recess communicating with the expansion chamber (24) of the actuator (11).
Charging device (100) for densifying porous preforms (160-163) of stackable shape in a reaction chamber of an infiltration furnace by controlled flow chemical vapour infiltration, the device comprising: - a support plate (110), - a first stack of a plurality of lower rings (140-144) placed on the support plate (110) and comprising a plurality of injection orifices extending between the outer periphery and the inner periphery of each ring, - a second stack of a plurality of upper rings (150-154) comprising a plurality of discharge orifices extending between the outer periphery and the inner periphery of each ring, - a first non-porous wall (130) of a shape and size identical to those of the porous preforms (160-163) that are to be densified and arranged on the support plate (110) inside the lower rings (140-144) of the first stack, said first non-porous wall extending between the support plate and the upper ring situated at the base of the second stack, - a second non-porous wall (170) of a shape and size identical to those of the porous preforms (160-163) that are to be densified, said second non-porous wall extending between the lower ring (143) situated at the top of the first stack and the upper ring (154) situated at the top of the second stack.
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for heating the substrate
C04B 35/00 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
79.
ELECTRICAL SWITCH FORMING A FAST ACTUATION CIRCUIT BREAKER
A normally closed electrical switch having a sliding assembly actuated on opening, for example by a pyrotechnic gas generator. Prior to actuation, a conductive portion of the sliding assembly (21) is in tight contact with two axially offset coaxial rings (13a, 14a) belonging respectively to two electrically conductive pads (13, 14), and after the actuator is triggered, the upstream pad (13) is released from the conductive portion of the sliding assembly. According to the invention, the sliding assembly comprises a tube provided with a slot extending along the entire length of same, and the conductive portion of the sliding assembly consists of all or a portion of said slotted tube, the clamping force between the conductive portion and the primary electrically conductive pads being provided by the elasticity of the slotted tube.
A device for atomising (100) a liquid (L), comprises a container (10) containing the liquid to be atomised (L), at least one liquid ejection member (20), in communication with said container (10), and a pyrotechnic gas generator (30) for pressurising the liquid inside said container and propelling said pressurised liquid out of said container. According to the invention, the ejection member (20) is, at least in one operating mode, in communication with the gas generator (30) in such a way as to be able to be supplied with the gas generated by said generator (30).
A62C 35/02 - Permanently-installed equipment with containers for delivering the extinguishing substance
A62C 13/70 - Portable extinguishers which are permanently pressurised or pressurised immediately before use with extinguishing material and pressure gas being stored in separate containers characterised by means for releasing the pressure gas
B05B 7/00 - Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas
B05B 7/04 - Spray pistols; Apparatus for discharge with arrangements for mixing liquids or other fluent materials before discharge
B05B 7/06 - Spray pistols; Apparatus for discharge with one outlet orifice surrounding another approximately in the same plane
A62C 31/07 - Nozzles specially adapted for fire-extinguishing with two or more outlets for different media
81.
Device for attaching blades to a turbine engine rotor disk
A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.
Method for producing a component made of composite comprising a fibrous reinforcement that is densified with a matrix, said method involving the following steps: - creation of a fibrous texture (10) by weaving filaments, said fibrous texture having a determined initial mean fibre content, - densification of the fibrous texture using a matrix. According to the invention, the fibrous texture (10) is, prior to densification, subjected to one or more jets (120) of water under pressure so as to reduce the mean fibre content in the texture to a value of between 20% and 45%.
D06C 29/00 - Finishing or dressing, of textile fabrics, not provided for in the other groups of this subclass
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
The invention relates to a method for the treatment of silicon carbide fibres, comprising a step involving the chemical treatment of fibres with an aqueous acid solution containing hydrofluoric acid and nitric acid but free of acetic acid in order to remove the silica present on the surface of fibres and to form a layer of microporous carbon. The invention also relates to a method for the production of a fibrous preform, comprising the formation of a fibrous structure comprising treated silicon carbide fibres and the use of said preform for the production of a part made from composite material.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
C23C 16/02 - Pretreatment of the material to be coated
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
The invention relates to a device (200) providing protection against lightning and intended to be placed on a structure (100) that is to be protected, and comprising: a surface coating comprising at least one coat of conducting paint (202), a plurality of electrically conducting elements (204) positioned in a spaced-apart manner on the structure, said elements being in contact with the coat of conducting paint (202), a protective coating (205) applied to the surface coating and comprising a thermally insulating and electrically conducting material, the protective coating (205) partially covering the electrically conducting elements (204).
The invention concerns an afterbody assembly (400) of an aircraft engine comprising an exhaust housing (100) made from a metal material comprising a plurality of arms (130) extending radially between an inner shell (110) and an outer shell (120). The assembly comprises at least one axisymmetric part (200) made from a composite material extending between an upstream end (201) secured to said exhaust housing (100) and a free downstream end (202). According to the invention, the axisymmetric part (200) comprises, at the upstream end (201) of same, an annular portion (210) comprising a plurality of slots (211) together delimiting a plurality of elastic fastening tabs (212). Each slot engages with an arm (130) of the exhaust housing which further comprises attachment portions (131) to which the elastic fastening tabs (212) are secured.
The invention concerns a holding tool (100) for at least one part (150) made from metal material intended to be heat treated or hot shaped, said tool comprising: - a fixed support structure (110) having a determined shape corresponding to the general shape of each part made from metal material to be held, - first holding elements (1161-1261) disposed to one side of each part, - second holding elements (1162-1262) disposed to the other side of each part, - at least one elastic spring element (130-134) placed between the support structure (110) and each first or second holding element (1161-1261; 1162-1262) so as to hold the part for the entire duration of a heat treatment. The support structure (110), the first and second holding elements (1161-1261, 1162-1262) and the elastic element or elements (130-134) are made from a thermostructural composite material.
A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.
The invention relates to a gas turbine aero engine afterbody assembly comprising a casing (40), an annular jet pipe (38) positioned in the downstream continuation of the casing, and a plurality of tubes (42) positioned around the jet pipe and intended to inject a fluid into the downstream end of the jet pipe, the jet pipe being fixed to the casing via the tubes.
F02K 1/34 - Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
The invention relates to an aeronautical engine exhaust cone (1) extending from upstream to downstream along a longitudinal axis. The cone (1) comprises a structural core (10) made of composite material formed of an axisymmetric component (11) which at its upstream end has an upstream flange (12) and at its downstream end has a downstream flange (13), the core providing the cone with its structural strength. The cone further comprises an acoustic attenuation system (20) made of a composite material and attached to the structural core (10).
The invention relates to a spacecraft (1), in particular a satellite or probe, which can be used to carry out high-thrust or high specific impulse movements. According to the invention, the spacecraft (1) includes at least one solid propellant motor (10-14) and at least one electric thruster (20-24).
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Lamouroux, Franck
Bertrand, Sébastien
Jacques, Sylvain
Louchet, Caroline
Abstract
The invention relates to a part made of a ceramic matrix composite comprising a fibrous reinforcement made of carbon or ceramic fibres, and a mainly ceramic sequenced matrix comprising first matrix layers made of a crack deviator alternating with second matrix layers made of a ceramic. An interphase coating is interposed between the fibres and the matrix, the interphase coating adhering to the fibres and to the matrix and being formed from at least one sequence consisting of a first elementary layer made of carbon, which is optionally doped with boron, surmounted with a second elementary layer made of a ceramic, the external elementary layer of the interphase coating being a ceramic layer the external surface of which is formed by ceramic grains the size of which essentially lies between 20 nanometres and 200 nanometres, with the presence of grains larger than 50 nanometres in size providing the external surface with a roughness ensuring mechanical bonding with the adjacent matrix phase.
C04B 35/563 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on boron carbide
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing 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
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Mazerat, Stéphane
Pailler, René
Loison, Sylvie
Philippe, Eric
Abstract
The invention relates to a method for treating silicon carbide fibres (20), comprising a reactive gaseous phosphation heat treatment such as to form, around each fibre (20), an oxidation-protective coating (200) including a surface layer of silicon pyrophosphate crystals (201) and at least one subjacent bilayer system (210) comprising a layer of a phosphosilicate glass (211) and a layer of microporous carbon (212).
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
Multilayer weaving is used to form a fiber blank having a longitudinal direction corresponding to the longitudinal direction of the vane to be made and comprising across its thickness a first woven portion (102) with a plurality of layers of yarns interlinked by weaving, and also a second woven portion and a third woven portion. The first portion is situated between the second and third portions to which it is interlinked by weaving over only a fraction of its longitudinal dimension. A preform for the vane to be made is formed by folding out, on either side of the first portion, segments (104a, 106a, 104b, 106b) of the second and third portions that are not interlinked with the first portion, by shaping the first portion to form a preform portion for the airfoil of the vane to be made, and by shaping the folded-out segments of the second and third portions to form preform portions for the inner and outer platforms of the vane to be fabricated, the vane preform being densified with a matrix in order to obtain a composite material vane having incorporated platforms.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
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 materials; Measures against erosion or corrosion
The invention relates to the manufacture of a composite material part, includes the steps of: creating a consolidated fibrous preform, the fibers of the preform being carbon or ceramic fibers and being coated with an interphase formed of at least one pyrolytic carbon (PyC) or boron-doped carbon (BC) layer; obtaining a partially densified, consolidated fibrous preform, the partial densification including the formation, on the interphase, of a first matrix phase including a plurality of layers of self-healing material alternating with one or more PyC or BC layers; and pursuing densification by scattering carbon and/or ceramic powder within the partially densified, consolidated preform and permeating with fused silicon or a liquid composition predominantly formed of silicon.
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
95.
HOLLOW-BLADE TURBINE VANE MADE FROM COMPOSITE MATERIAL, TURBINE OR COMPRESSOR INCLUDING A NOZZLE OR GUIDE VANE ASSEMBLY FORMED BY SUCH BLADES, AND TURBOMACHINE COMPRISING SAME
A turbomachine vane (10) made from composite material comprises a hollow blade (12) including an internal passage (11) extending along the entire length thereof, an internal platform (14) and an external platform (16). The blade is extended on the external side of the external platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing, said attachment portions being formed by attachment lugs (24, 26, 28) extending from external longitudinal ends of lower surface (12a) and upper surface (12b) walls of the blade, with the fibrous reinforcement texture of the composite material extending continuously between said walls and the attachment lugs.
F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
F01D 9/06 - Fluid supply conduits to nozzles or the like
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
96.
HOLLOW-BLADE TURBINE VANE MADE FROM COMPOSITE MATERIAL, TURBINE OR COMPRESSOR INCLUDING A NOZZLE OR GUIDE VANE ASSEMBLY FORMED BY SUCH BLADES, AND TURBOMACHINE COMPRISING SAME
A turbomachine vane (10) made from composite material comprises a hollow blade (12) including an internal passage (11) extending along the entire length thereof, an internal platform (14) and an external platform (16). The blade is extended on the external side of the external platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing, said attachment portions being formed by attachment lugs (24, 26, 28) extending from external longitudinal ends of lower surface (12a) and upper surface (12b) walls of the blade, with the fibrous reinforcement texture of the composite material extending continuously between said walls and the attachment lugs.
According to the invention, a fibrous blank is formed by means of multilayer weaving, said blank having a longitudinal direction corresponding to that of the vane to be produced and the thickness thereof comprising a first portion (102) with multiple interwoven layers of yarns, a second woven portion and a third woven portion. The first portion is located between the second portion and the third portion and it is interwoven therewith along only part of the longitudinal dimension thereof. A preform of the vane to be produced is formed by unfolding, on both sides of the first portion, segments (104a, 106a, 104b, 106b) of the second and third portions that are not connected to the first portion, by shaping the first portion in order to form a preform part for the blade of the vane to be produced, and by shaping the unfolded segments of the second and third portions in order to form preform parts for the internal and external platforms of the vane to be produced, and the vane preform is densified using a matrix in order to obtain a vane made from composite material and including integrated platforms.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
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
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
98.
A METHOD OF FABRICATING A TURBINE OR COMPRESSOR GUIDE VANE SECTOR MADE OF COMPOSITE MATERIAL FOR A TURBINE ENGINE, AND A TURBINE OR A COMPRESSOR INCORPORATING SUCH GUIDE VANE SECTORS
Single-airfoil vanes each having an inner platform (114), an outer platform (116), and an airfoil (118) are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes are assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together by a process including at least one step selected from: a step of bonding by brazing; and a step of bonding by co- densification with a matrix. The inner or outer platform of a first vane comprising an inner or outer passage- constituting platform portion that is bonded to an inner or outer platform portion of an adjacent second vane in a bonding zone extending over at least a portion of the inside surface of the inner passage-constituting platform portion of the first vane and/or over at least a portion of inner surface of the outer passage-constituting platform portion of the first vane.
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
The invention relates to a attachment device (240) for attaching a hollow part consisting of two opposing walls to at least one structural part. The device includes a one-piece body (241) made of a metal material and having two main surfaces (242, 243) extending longitudinally between first and second ends (244, 245) of said body. Each main surface (242; 243) includes a bearing portion (2420; 2430) in the vicinity of the first end (244) of said body, which bearing portion is intended to be pressed against an inner surface of one of the two walls of the hollow part, each bearing portion (2420; 2430) comprising an attachment opening (2421) for receiving an attachment member. The bearing portions (2420; 2430) are separated from one another by a slot (246) extending from the first end (244) of said body (241) to a predetermined depth in said body.
Single blade vanes each having an inner platform (114), an outer platform (116) and a blade (118) are obtained by three-dimensional weaving of a fibrous blank formed as a single piece, by shaping the fibrous blank to obtain a one-piece fibrous preform, by densifying the preform with a matrix to obtain a composite vane forming a single piece with built-in inner and outer platforms. Several vanes are assembled and joined together to form a composite multi-blade turbine nozzle guide vanes sector or compressor guide vanes sector, connection being achieved through a process involving at least one step chosen from: a step of connection using brazing and a step of connection using codensification with a matrix of vanes that are assembled at an intermediate stage in their densification. The inner or outer platform of a first vane comprises an inner or outer platform part that makes up part of the shroud and is connected to an inner or outer platform part of an adjacent second vane in a connecting zone extending over at least part of the interior surface of the inner platform part that makes up part of the shroud of the first vane and/or over at least part of the outer surface of the outer platform part that makes up the shroud of the first vane.
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
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
patents
