HERAKLES Patent applications |
Patent application number | Title | Published |
20160131459 | PYROTECHNICAL GAS GENERATOR - A pyrotechnic gas generator for driving an actuator includes a body defining a combustion chamber housing a main pyrotechnic charge, and an ignitor for initiating combustion of the main pyrotechnic charge. The pyrotechnic gas generator includes at least one delay chamber adapted to communicate with the combustion chamber via at least one inlet orifice, and the delay chamber is provided with at least one outlet orifice for passing gas out from the gas generator. The at least one outlet orifice is provided with a seal adapted to pass from a closed state to an open state when the pressure inside the delay chamber reaches a rupture limit pressure. | 05-12-2016 |
20160108744 | ROTOR DISK BLADE WITH FRICTION-HELD ROOT, ROTOR DISK, TURBOMACHINE AND ASSOCIATED ASSEMBLY METHOD - A rotor disk blade for a turbine engine, the blade being made of composite material including fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a portion constituting an airfoil and a blade root forming a single piece, the blade root having two substantially plane opposite lateral flanks that are formed respectively extending the pressure side surface and the suction side surface of the airfoil. The blade root is clamped between two metal plates fastened against the lateral flanks of the blade root by a bolt and a nut passing through the plates and the blade root. The bolt has a head bearing against one of the two plates. The nut has a head bearing against the other plate. | 04-21-2016 |
20160001898 | SPACE PROPULSION MODULE HAVING BOTH ELECTRIC AND SOLID FUEL CHEMICAL PROPULSION - A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster ( | 01-07-2016 |
20150298079 | KNEADING DEVICE FITTED WITH A SHAFT RETENTION DEVICE - A paste kneading device includes an oblong barrel, two shafts arranged parallel within the barrel, being held and driven at their first ends, defining an upstream end, by a drive device, two screws each formed by threads carried by the shafts, each screw having a transport section carrying a main thread to cause the paste to advance along the two screws, and an outlet orifice formed in the wall of the barrel to discharge the kneaded paste, the kneading device further including a holder device to hold each shaft at its second end, defining a downstream end, and enabling the shaft to rotate freely, the holder device including, for each shaft, a first portion secured to the shaft and a second portion secured to a cap end portion of the barrel, the cap end portion being removable and the first and second portions being configured to engage and disengage freely. | 10-22-2015 |
20150247412 | TURBINE ENGINE BLADE MADE OF COMPOSITE MATERIAL WITH A BULB-SHAPED ROOT - A turbine engine blade made of composite material including fiber reinforcement obtained by three dimensionally weaving yarns and densified with a matrix, the blade including an airfoil and a blade root forming a single part. The blade root includes two opposite lateral flanks that are substantially plane and that are clamped between two independent pads made of composite material, which pads are fastened against the lateral flanks of the blade root to form a blade root that is bulb-shaped. | 09-03-2015 |
20150175487 | Ultra-Refractory Material that is Stable in a Wet Environment, and Process for Manufacturing Same - A refractory material withstanding high temperatures in an oxidizing medium contains at least hafnium boride and tantalum boride, hafnium and tantalum being present in the refractory material exclusively in compound form. | 06-25-2015 |
20150174703 | METHOD FOR THE BRAZING OF PARTS MADE FROM A COMPOSITE MATERIAL, INCORPORATING A SLUG IN THE BOND - A method of assembling together by brazing first and second parts made of composite material, each of the first and second parts having an assembly face for brazing with the assembly face of the other part, the method including making at least one perforation in the assembly face of the first part; interposing capillary elements between the assembly faces of the first and second parts made of composite material; placing the first and second parts facing each other while inserting a peg in each perforation of the first part; placing a brazing composition in contact with a portion of the capillary elements; and applying heat treatment to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity between the assembly faces of the composite material parts. | 06-25-2015 |
20150075428 | Device for Loading Porous Substrates of Three-Dimensional Shape in Order to be Densified by Directed Flow Chemical Vapor Infiltration - A loader device for loading porous substrates of three-dimensional shapes extending mainly in a longitudinal direction into a reaction chamber of an infiltration oven for densification of the preforms by directed flow chemical vapor infiltration. The device comprising at least one annular loader stage formed by first and second annular vertical walls arranged coaxially relative to each other and defining between them an annular loader space for the porous substrates to be densified. First and second plates respectively cover the bottom portion and the top portion of the annular loader space. The first and second annular vertical walls include support elements arranged in the annular loader space so as to define between them unit loader cells, each for receiving a respective substrate to be densified. The device also comprises gas feed orifices and gas exhaust orifices in the vicinity of each unit loader cell. | 03-19-2015 |
20150040396 | METHOD OF FABRICATING A COMPOSITE MATERIAL TURBINE ENGINE VANE WITH INCORPORATED PLATFORMS - 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 with a plurality of layers of yarns interlinked by weaving, and also a second and third woven portions. The first portion is situated between the second and third portions and interlinked thereto by weaving over only a fraction of its longitudinal dimension. A preform for the vane is formed by folding out, on either side of the first portion, segments of the second and third portions not interlinked with the first portion, by shaping the first portion to form a preform portion for the airfoil of the vane, 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. | 02-12-2015 |
20140363663 | CMC MATERIAL PART - A part made of ceramic matrix composite material has fiber reinforcement of carbon or ceramic fibers and a majority-ceramic sequenced matrix having first matrix layers made of crack-deflector material alternating with second matrix layers made of ceramic material. An interphase coating is interposed between the fibers and the matrix, and the interphase coating adheres to the fibers and to the matrix, and is formed of at least one sequence constituted by a first elementary layer made of carbon, possibly doped with boron, surmounted by a second elementary layer made of ceramic. The outer elementary interphase layer of the coating is a ceramic layer having an outer surface formed by ceramic grains of size lying essentially in the range 20 nm to 200 nm, with the presence of grains of size greater than 50 nm conferring roughness on the outer surface ensuring mechanical attachment with the adjacent matrix phase. | 12-11-2014 |
20140356094 | ASSEMBLY PROVIDING A CONNECTION THAT IS SELF TIGHTENING WITH TEMPERATURE - An assembly comprising first and second parts made of composite material held one against the other by at least one fastener system comprising a bolt having a flat head from which there extends a threaded portion, and a nut having a flat head from which there extends a shank including tapping suitable for co-operating with the threaded portion of the bolt. The head of the bolt bears against a countersink formed in the first part. The head of the nut bears against a countersink formed in the second part. The fastener system is suitable, during axial expansion of the fastener system, for causing each head to tilt towards the countersink in which it is housed. | 12-04-2014 |
20140332604 | Device for Fastening a Hollow Part - A fastener device for fastening a hollow part is made up of two mutually facing walls to at least one structural part. The device comprises a one-piece body of metal material presenting two main faces extending longitudinally between first and second ends of the body. Each main face includes a bearing portion in the vicinity of the first end of the body. The bearing portion is for being pressed against an inside surface of a respective one of the two walls of the hollow part, with each bearing portion including a fastener orifice for receiving a fastener member. The bearing portions are separated from each other by a slot extending from the first end of the body and over a determined depth within the body. | 11-13-2014 |
20140314556 | 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, an outer platform, and an airfoil 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 is 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. | 10-23-2014 |
20140287912 | Process for Preparing a Monolithic Catalysis Element Comprising a Fibrous Support and Said Monolithic Catalysis Element - A process for preparing a monolithic catalysis element includes a fibrous support and a catalytic phase supported by the fibrous support and also the monolithic catalysis element. The process includes the steps of preparing a porous coherent structure based on refractory fibers; preparing a substrate including the porous coherent structure and nanocarbon supported by the porous coherent structure in the body thereof; and grafting to the substrate, by π interaction, of at least one aromatic compound containing in its chemical formula, at least one aromatic ring, and at least one function chosen from acid catalytic functions, basic catalytic functions, metallic precursor functions, functions that can be converted in situ into metallic precursor functions, and mixtures thereof. | 09-25-2014 |
20140235788 | METHOD FOR EXTRACTING SOLID SOLUBLE CHARGES CONTAINED IN A PASTE - The main subject of the present invention is a process for processing a paste ( | 08-21-2014 |
20140205463 | Turbine Engine Rotor Including Blade Made of Composite Material and Having an Added Root - A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element. | 07-24-2014 |
20140162156 | ON-BOARD ELECTRICITY PRODUCTION SYSTEM USING A FUEL CELL - The invention relates to an electricity production system for feeding electrical energy to a device of an aircraft. The system comprises a generator for generating gaseous hydrogen from hydrogen in non-gaseous form, a main tank connected upstream to the generator and for containing gaseous hydrogen under a pressure substantially higher than atmospheric pressure, the gaseous hydrogen being produced by the generator, at least one fuel cell, an expander connected upstream to the main tank and downstream to the fuel cell(s), where upstream and downstream are defined relative to the flow direction of the hydrogen under normal conditions of operation of the system, and a control device that regulates the flow rate and the pressure of the gaseous hydrogen from the main tank to the fuel cell(s) via the expander. | 06-12-2014 |
20140147375 | SELF-REGULATED PRODUCTION, UNDER SUBMERGED CONDITIONS, OF A GAS GENERATED BY CHEMICAL REACTION BETWEEN A LIQUID AND SOLID; ASSOCIATED DEVICE - The present invention relates to a process for the self-regulated production as a function of the demand, under submerged conditions, of a gas (G), said gas (G) being generated by a chemical reaction between a liquid (L) and a solid (S) (hydrogen generated by hydrolysis of a metal hydride, for example) and not being polluted between the generation thereof and the delivery thereof. The present invention also relates to a device suitable for the implementation of said process. | 05-29-2014 |
20140147264 | 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. | 05-29-2014 |
20140116584 | PYROTECHNIC GAS GENERATOR COMPOUNDS - The main subject of the present invention is solid pyrotechnic gas generator compounds, the composition of which contains: guanidine nitrate, basic copper nitrate, and at least one inorganic titanate, the melting point of which is above 2100 K. Said compounds are perfectly suitable for use in frontal airbags. | 05-01-2014 |
20140109552 | In-Flight Attitude Control and Direct Thrust Flight Control System of a Vehicle and Craft Comprising Such a System - A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle. | 04-24-2014 |
20140073781 | PROCESS FOR OBTAINING A CHARGE OF HEXANITROHEXAAZAISOWURTZITANE CRYSTALS HAVING A ROUNDED MORPHOLOGY; CHARGE AND CORRESPONDING ENERGETIC MATERIAL - The present invention provides a process for obtaining a charge of hexanitrohexaazaisowurtzitane crystals having rounded morphology. It also provides said charge, the energetic material comprising it, and a process for manufacturing said material. Said process for obtaining said charge comprises:
| 03-13-2014 |
20140072805 | MATERIALS AND PARTS THAT CAN WITHSTAND HIGH TEMPERATURES IN AN OXIDIZING MEDIUM, AND METHOD FOR MANUFACTURING SAME - A refractory material that can withstand high temperatures in an oxidizing medium and containing at least:
| 03-13-2014 |
20140072443 | Composite Turbomachine Blade with In-Built Root - A turbine engine blade of composite material comprising fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a first portion constituting an airfoil forming a single piece with at least one second portion constituting a blade root. The fiber reinforcement portions corresponding to the first and second portions of the blade are mutually interleaved, at least in part, with yarns of the second fiber reinforcement portion penetrating into the first fiber reinforcement portion. | 03-13-2014 |
20140030076 | TURBINE ENGINE BLADE OR VANE MADE OF COMPOSITE MATERIAL, TURBINE NOZZLE OR COMPRESSOR STATOR INCORPORATING SUCH VANES AND METHOD OF FABRICATING SAME - 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. | 01-30-2014 |
20130310238 | COMPOSITE MATERIAL ROLLER FOR HIGH-TEMPERATURE ANNEALING - A roller for a high temperature annealing line includes a cylindrical shell and an axial support element and including a spindle at at least one of its ends, and first and second keys fastened to the axial support element and each arranged in a respective first or second through opening formed in the shell. The first key is mounted to bear against a first circumferential bearing surface of the first through opening while the second key is mounted against a second circumferential bearing surface of the second through opening opposite to the first circumferential bearing surface of the first through opening in a circumferential travel direction. The first key is mounted to bear against the second longitudinal bearing surface of the first through opening, while the second key is mounted against the first longitudinal bearing surface of the second through opening opposite to the second longitudinal bearing surface. | 11-21-2013 |
20130302171 | DEVICE FOR ATTACHING BLADES TO A TURBINE ENGINE ROTOR DISK - The invention provides a device for attaching blades to a rotor disk of a turbine engine, comprising: a rotor disk provided at its outer periphery with a plurality of slots, each 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. | 11-14-2013 |
20130252191 | TOOLING FOR SUPPORTING METAL PARTS DURING HEAT TREATMENT - A support tooling for supporting at least one metal part that is to be subjected to heat treatment or shaped while hot, the tooling including: a stationary support structure presenting a determined shape that corresponds to the general shape of each metal part that is to be supported; first holder elements arranged on one side of each part; second holder elements arranged on the other side of each part; and at least one spring type resilient element placed between the support structure and each first or second holder element so as to hold the part throughout the duration of heat treatment. The support structure, the first and second holder elements and the resilient element(s) are made of thermostructural composite material. | 09-26-2013 |
20130243604 | TURBOMACHINE BLADES OR VANES HAVING COMPLEMENTARY EVEN/ODD GEOMETRY - A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate. | 09-19-2013 |
20130230404 | METHOD OF OPTIMIZING THE PROFILE OF A COMPOSITE MATERIAL BLADE FOR ROTOR WHEEL OF A TURBINE ENGINE, AND A BLADE HAVING A COMPENSATED TANG - 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. | 09-05-2013 |
20130228254 | PYROTECHNIC GAS GENERATOR COMPOUNDS - The main subject of the present invention is a solid pyrotechnic gas generator compound, the composition of which contains, expressed in weight percentages:
| 09-05-2013 |
20130139508 | TRIGGERED-STROKE ACTUATOR PROVIDED WITH A GAS DISCHARGE DEVICE - The invention relates to a triggered-stroke actuator ( | 06-06-2013 |
20130126326 | ELECTRIC SWITCH HAVING A SLIDE AND FORMING A SHORT-CIRCUIT OR SELECTOR SWITCH - The present invention relates to an electric switch having a hollow body defining a cavity, an actuator, and a slide mounted in said cavity. Under the action of the actuator, the slide is suitable for passing from a first position, in which at least one conductive portion of the slide is electrically connected via permanent breakable electrical junctions to at least two primary electrically-conductive studs that lead laterally into said cavity to a second position in which at least one of said primary electrically-conductive studs is no longer electrically connected to said conductive portion of the slide. | 05-23-2013 |
20130121905 | METHOD FOR OBTAINING BORAZANE, SUITABLE FOR OBTAINING HIGHLY PURE AND VERY HIGHLY PURE BORAZANE - The present invention relates to a method for obtaining borazane, said method being suitable for obtaining borazane containing a low level of impurities. The borazane (obtained by reaction of at least one ammonium salt with at least one alkali and/or alkaline earth metal borohydride) in solution in THF is selectively precipitated with a non-solvent. The precipitated borazane can further be purified by selective dissolution. The borazane obtained after selective precipitation and dissolution contains less than 1% by weight of impurities and/or does not exhibit exothermic decomposition in the solid state with a temperature range of the endothermic melting peak above 110° C. | 05-16-2013 |
20130101429 | TURBOMACHINE BLADE OR VANE HAVING COMPLEMENTARY ASYMMETRICAL GEOMETRY - A turbomachine blade is made of composite material. The blade includes a first portion constituting at least an airfoil exhibiting two faces each connecting a leading edge to a trailing edge, the first portion forming a single part with at least one second portion present only on one of the faces of the airfoil. The second portion constitutes a portion of at least one of the following elements: a flowpath delimiting outer portion of an inner platform, an inner portion of an inner platform, a flowpath delimiting inner portion of an outer platform, and an outer portion of an outer platform. Portions of fiber reinforcements corresponding to the first and the second portions of the blade are at least partially mutually imbricated. Yarns of the first portion of the fiber reinforcement penetrate into the second portion of the fiber reinforcement. | 04-25-2013 |
20130089429 | TURBINE ENGINE BLADE MADE OF COMPOSITE MATERIAL, AND A METHOD OF FABRICATING IT - A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: 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 a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein. | 04-11-2013 |
20130056344 | ELECTRIC CIRCUIT BREAKER WITH PYROTECHNIC ACTUATION - An electric switch constituting a circuit breaker in particular, wherein a conductive blade is broken by the tripping of a pyrotechnically actuated gas generator. | 03-07-2013 |
20130028746 | TURBINE ENGINE TURBINE BLADE MADE OF A CERAMIC-MATRIX COMPOSITE WITH RECESSES MADE BY MACHINING - A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece. | 01-31-2013 |
20130019586 | PROPULSION METHOD AND DEVICE COMPRISING A LIQUID OXIDANT AND A SOLID COMPOUND - One subject of the present invention is a propulsion method comprising:
| 01-24-2013 |
20120328415 | VIBRATION DAMPER COMPRISING A PEG BETWEEN OUTER PLATFORMS OF ADJACENT COMPOSITE-MATERIAL BLADES OF A TURBINE ENGINE ROTOR WHEEL - A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts. | 12-27-2012 |
20120323017 | DINITROPYRAZOLE DERIVATIVES, THEIR PREPARATION, AND ENERGETIC COMPOSITIONS COMPRISING THEM - The present invention provides:
| 12-20-2012 |
20120318065 | MONITORING DEVICE FOR A VISCOELASTIC MATERIAL - A device for monitoring a viscoelastic material by subjecting the sample to vibration and analyzing the response of the sample to such vibration. According to the invention, the sample ( | 12-20-2012 |