Verfahren zur Herstellung der beta-Modifikation von Hexanitrohexaazaisowurtzitan

Verfahren zur Herstellung der -Modifikation von Hexanitrohexaazaisowurtzitan durch Herstellung einer Lösung einer beliebigen der polymorphen Formen von Hexanitrohexaazaisowurtzitan in Tetrahydrofuran, Ausfällung der -Modifikation von Hexanitrohexaazaisowurtzitan durch Zugabe eines halogenhaltigen Lösungsmittels als Fällungsmittel zu der Lösung und Isolierung der ausgefällten -Modifikation von Hexanitrohexaazaisowurtzitan aus dem Medium.

A CMC MIXER HAVING A STRUCTURAL OUTER COWLING

The invention relates to a mixer (100) for the separated-flow nozzles of a turbojet, for mixing a hot inner flow from the turbojet combustion chamber with the cold outer flow from the turbojet fan. The mixer includes an inner shell (120) defining a flow channel for said hot inner flow, an outer shell (110) provided around the inner shell (120) and defining therewith a flow channel for said cold outer flow, and a lobe structure in which the lobes (1321, 1322) extend longitudinally from the trailing edges (HOa, 120a) of said shells. The lobe structure (130) is made of a ceramic-matrix composite material and is connected to the outer shell (110) by flexible connection tabs (140).

A CHEMICAL VAPOR INFILTRATION METHOD FOR DENSIFYING POROUS SUBSTRATES WITH PYROLYTIC CARBON

... ²²One or more porous substrates for densification (10) ²are loaded into an oven (12) into which there is admitted ²a reaction gas containing a pyrolytic carbon precursor ²gas comprising at least one gaseous hydrocarbons C x H y in ²which x and y are integers and x is such that 1 < x < 6, ²together with a vector gas comprising at least one gas ²selected from methane and inert gases. Effluent gas ²containing residual components of the admitted gas ²together with reaction products, including hydrogen, is ²extracted from the oven and at least a fraction of a gas ²stream extracted from the effluent gas and containing ²pyrolytic carbon precursor reagent gas is recycled ²(circuit 80) into the reaction gas admitted into the ²oven, the recycling being performed after eliminating ²heavy hydrocarbons (treatment 40) contained in the ²effluent gas.² ...

ASSEMBLY HAVING A TEMPERATURE-DEPENDENT SELF-TIGHTENING CONNECTION

L'invention concerne un assemblage (100) comprenant une première pièce (10) et une deuxième pièce (20) en matériau composite maintenues l'une contre l'autre par au moins un système de fixation (50) comprenant un rivet (30) comportant une tête fraisée (31) à partir de laquelle s'étend une tige (32) comportant une extrémité élargie (320) et une rondelle (40) coopérant avec l'extrémité élargie (320) de la tige (32) du rivet (30). La tête (31) du rivet (30) est en appui contre une fraisure (12) ménagée dans la première pièce (10), la rondelle (40) étant en appui sur la deuxième pièce (20). La rondelle (40) présente sur sa face (43) opposée à celle (42) en appui sur la deuxième pièce (20) une portion de forme conique (430). La rondelle (40) comporte en outre une fraisure centrale (410) sur la surface de laquelle repose l'extrémité élargie (320) de la tige (32) du rivet (30).

SYSTEM AND METHOD FOR THE EMERGENCY STARTING OF AN AIRCRAFT TURBOMACHINE

Système (20) de démarrage d'urgence de turbomachines d'aéronef, comprenant au moins un générateur de gaz (22) à propergol solide, un dispositif d'allumage (24) commandé électriquement, un calculateur (28) relié au dispositif d'allumage, et au moins deux démarreurs (18) indépendants destinés chacun au démarrage d'une turbomachine, chaque démarreur comportant une turbine (38) d'entraînement d'un arbre (34) destiné à être couplé à un arbre (54) de la turbomachine correspondante, la sortie des gaz du générateur étant reliée à l'entrée (44) de la turbine de chaque démarreur par une même vanne de distribution (26) reliée au calculateur (28).

A 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 (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 ...

PYROTECHNIC PRODUCT HIGH PERFORMANCE COMPOSITE PB IN ITS COMPOSITION AND ITS PREPARATION

La présente invention a pour principal objet un produit pyrotechnique composite, performant, sans plomb dans sa composition, dont l'obtention à l'échelle industrielle ne se heurte pas à un problème de vie de pot de la pâte intermédiaire. Ledit produit renferme, dans un liant plastifié, comprenant un polymère énergétique réticulé et au moins un plastifiant énergétique, des charges énergétiques organiques et un catalyseur de combustion. De façon caractéristique, ledit polymère énergétique réticulé consiste en un polyazoture de glycidyle (PAG), ayant une masse moléculaire moyenne en nombre (Mn) comprise entre 700 et 3000 g/mol, réticulé, via ses fonctions terminales hydroxyles, avec au moins un agent de réticulation de type polyisocyanate, et ledit catalyseur de combustion consiste en le citrate de bismuth.

CVI DENSIFICATION INSTALLATION COMPRISING A PREHEATING AREA HIGHLY

Une installation de traitement thermochimique (100) comprend une chambre de réaction (140), au moins une entrée de gaz (104), une chambre de préchauffage de gaz (110) située entre l'entrée de gaz (104) et la chambre de réaction (140). La chambre de préchauffage (110) comprend plusieurs plateaux de distribution perforés (111-114) maintenus de manière espacée les uns au-dessus des autres. La chambre de préchauffage (110) comprend en outre, entre au moins les plateaux de distribution en vis-à-vis, une pluralité de parois (1110, 1120, 1130) définissant entre lesdits plateaux (111-114) des chemins de circulation pour un flux gazeux. A thermochemical treatment plant (100) comprises a reaction chamber (140), at least one gas inlet (104), a gas preheating chamber (110) located between the gas inlet (104) and the gas chamber (104). reaction (140). The preheating chamber (110) comprises a plurality of perforated distribution trays (111-114) spaced apart one above the other. The preheating chamber (110) further comprises, between at least the distribution trays facing each other, a plurality of walls (1110, 1120, 1130) defining between said trays (111-114) circulation paths for a gas flow.

THIN COMPOSITE EXPLOSIVE PRODUCTS AND THEIR PREPARATION

La présente invention concerne des produits explosifs composites et leur préparation. Lesdits produits présentent : - une composition, exprimée en pourcentages massiques, qui renferme : + de 85 à 92 %, avantageusement de 88 à 90 %, de charges énergétiques organiques ; lesdites charges énergétiques organiques a) étant choisies parmi des charges d'octogène (HMX), d'hexogène (RDX), d'hexanitrohexaazaisowurtzitane (CL20), de pentrite (PETN) et leurs mélanges et b) présentant une distribution granulométrique avec une valeur de D90 inférieure à 15 µm et une valeur de D50 inférieure ou égale à 5 µm ; et + de 7 à 12 %, avantageusement de 8 à 10 %, d'une gomme polymérique choisie parmi les gommes polyuréthane-polyester, les gommes polyuréthane-polyéther et leurs mélanges, dont la masse moléculaire moyenne en nombre est supérieure à 20 000 g/mol et dont la viscosité Mooney est comprise entre 20 et 70 ML (5 + 4) à 100°C ; et - une épaisseur de 0,4 à 5 mm, avantageusement de 1 à 2 mm. Lesdits produits ...

ROTATING ASSEMBLY FOR A TURBOMACHINE COMPRISING A STATOR RING SELF-DOOR

Le présent exposé concerne un ensemble rotatif pour turbomachine permettant un meilleur contrôle du jeu radial entre deux pièces coaxiales. Il comprend un rotor comportant au moins deux étages rotoriques consécutifs (10a, 10b) munis d'une pluralité d'aubes mobiles (20), et une virole de rotor (50), annulaire, reliant lesdits deux étages rotoriques consécutifs (10a, 10b) ; un stator comportant au moins un étage statorique (11), muni d'une pluralité d'aubes fixes (30), prévu entre lesdits deux étages rotoriques consécutifs (10a, 10b), et un anneau de stator (60), annulaire, monté sur lesdites aubes fixes (30) ; l'un (50) des éléments parmi la virole de rotor et l'anneau de stator porte au moins une léchette (51) configurée pour coopérer avec une piste abradable (21) portée par l'autre (60) desdits éléments ; l'anneau de stator (60) est monté sur les aubes fixes (30) par l'intermédiaire d'un dispositif d'accrochage mettant en jeu une pluralité de fentes radiales (66), chaque fente étant pratiquée ...

THERMAL SAFETY DEVICE

DEVICE AND PROCESS FOR THE FILLING OF STRUCTURE OF ENGINE HAVE RETURNING SUBGRADES

PROTECTIVE SYSTEM OF the Lower extremities Of an OCCUPANT Of a VEHICULEAUTOMOBILE

MANUFACTORING PROCESS Of a COMPOSITE MATERIAL PART THERMOSTRUCTURAL

GAS GENERATOR AND TURBINE ENGINE EQUIPPED WITH SUCH GENERATOR FOR STARTING

ATTACHMENT UNIT Of a LINEAR JACK IN ROTATION

CHEMICAL PROCESS Of INFILTRATION IN GAS PHASE FOR the THICKENING OF POROUS SUBSTRATES BY PYROLYTIC CARBON

MANUFACTORING PROCESS OF COMPOSITE MATERIAL PART HAS CERAMIC MATRIX CONTAINING OF THE PHASES OF HEALING AND DEVIATIVE MATRIX CRACKS

CONTINUOUS PROCESS OF MANUFACTURE WITHOUT SOLVENT OF COMPOSITE PYROTECHNICAL PRODUCTS

PROCESS OF SYNTHESIS OF THE MONOCHLORAMINE

METHOD FOR MAKING A FILTER WITH INTEGRATED PIN IN THE CONNECTION

ASSEMBLY TEMPERATURE SELF-CLAMPING CONNECTION

TURBINE RING ASSEMBLY OF COMPOSITE MATERIAL WITH CERAMIC MATRIX

L'invention concerne un ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau (1) en une seule pièce en matériau composite à matrice céramique destiné à être monté sur une structure de support d'anneau (3), la structure de support d'anneau comprenant deux pattes (32, 34) s'étendant radialement vers une veine d'écoulement du flux gazeux, chaque secteur d'anneau ayant une première partie formant base annulaire (12) avec une face radialement interne définissant la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent deux parties formant pattes (14, 16), les secteurs d'anneau ayant une section sensiblement en forme de π. Les pattes de chaque secteur d'anneau sont aptes à enserrer axialement les pattes de la structure de support d'anneau, et à être maintenues à celles-ci par l'intermédiaire de pions (40) traversant de part en part des trous (14a, 14b, 14c, 16b) pratiqués dans les pattes de chaque secteur d'anneau et venant se loger dans ...

ROTOR FOR TURBOSHAFT ENGINE

TOGETHER Of RING OF TURBINE

MANUFACTORING PROCESS Of a COMPOSITE MATERIAL PART THERMOSTRUCTURAL AND PART THUS OBTAINED

INFILTRATION PROCESS OR CHEMICAL VAPOR DEPOSITION

La présente invention concerne un procédé d'infiltration ou de dépôt chimique en phase vapeur comprenant au moins l'étape suivante : - formation de carbure de silicium dans la porosité d'un substrat poreux ou sur une surface d'un substrat, le substrat étant placé dans une enceinte réactionnelle, le carbure de silicium étant formé à partir d'une phase gazeuse introduite dans l'enceinte réactionnelle, cette phase gazeuse comprenant un composé réactif précurseur de carbure de silicium ayant la formule suivante : dans laquelle : - n est un entier égal à 0 ou 1, - m est un entier compris entre 1 et 3, - p est un entier compris entre 0 et 2 avec m + p = 3, et - R désigne -H ou -CH3, le rapport C/Si entre le nombre d'atomes de carbone et le nombre d'atomes de silicium dans la phase gazeuse introduite étant compris entre 2 et 3.

FASTENING Of a HOLLOW PART

Dispositif de fixation (240) destiné à fixer une pièce creuse formée de deux parois en regard l'une de l'autre sur au moins une pièce de structure. Le dispositif comprend un corps monolithique (241) en matériau métallique présentant deux faces principales (242, 243) s'étendant longitudinalement entre une première et deuxième extrémités (244, 245) dudit corps. Chaque face principale (242 ; 243) comprend au voisinage de la première extrémité (244) dudit corps une portion d'appui (2420 ; 2430) destinée à être plaquée sur une surface interne d'une des deux parois de la pièce creuse, chaque portion d'appui (2420 ; 2430) comportant un orifice de fixation (2421) destiné à recevoir un organe de fixation. Les portions d'appui (2420 ; 2430) sont séparées l'une de l'autre par une fente (246) s'étendant à partir de la première extrémité (244) dudit corps (241) et sur une profondeur déterminée dans ledit corps.

SHAPER FOR CONSOLIDATION AND/OR DENSIFYING GAS-PHASE FIBROUS PREFORM

L'invention concerne un conformateur pour la consolidation et/ou la densification en phase gazeuse d'une préforme fibreuse comportant : - une pluralité de blocs définissant une empreinte donnant sa forme à une pièce à obtenir après consolidation et/ou densification en phase gazeuse d'une préforme fibreuse, les blocs étant positionnés les uns par rapport aux autres à l'aide d'une pluralité d'éléments de positionnement, et - un système de protection permettant de protéger au moins une surface du conformateur d'un dépôt de la phase gazeuse, ledit système de protection permettant de protéger d'un dépôt de la phase gazeuse au moins : o une zone d'entrefer définie entre deux blocs, et/ou ○ une zone de fixation d'un élément de positionnement, et/ou o une pluralité de zones de référence pour le recalage de la forme des blocs, ces zones de référence étant situées sur la surface des blocs.

METHOD OF MANUFACTURING A COMPOSITE MATERIAL

L'invention concerne un procédé de fabrication d'un matériau composite comportant les étapes suivantes : a) réalisation d'une ou plusieurs opérations textiles mettant en oeuvre une pluralité de tresses (1) comportant chacune une pluralité de fils (21 ; ... ; 2n) tressés autour d'une âme (3) pour former une préforme fibreuse comportant lesdites tresses (1), et b) formation d'une phase de matrice dans la porosité de la préforme fibreuse, tout ou partie de la phase de matrice étant formée par transformation des âmes (3) des tresses (1).

PART OF COMPOSITE MATERIAL

La présente invention concerne une pièce en matériau composite comprenant au moins : - un renfort fibreux comprenant des fibres de carbure de silicium présentant une teneur en oxygène inférieure ou égale à 1% en pourcentage atomique, et - une matrice présente dans la porosité du renfort fibreux et comprenant au moins un silicate de terre rare, de la mullite ou un mélange de mullite et d'au moins un silicate de terre rare.

SET [...]-BODIES GAS TURBINE AEROENGINE

PADDLE OF MATERIAL TURBOSHAFT ENGINE COMPOSITE AND PROCEEDED FOR SA MANUFACTURE

MAINTENANCE TOOLS, LOADING AND INSTALLATION FOR DENSIFYING POROUS PREFORM OF REVOLUTION

METHOD OF MANUFACTURING TAPE APPLICATOR

PROCESS FOR MANUFACTURING A PART MADE OF A CERAMIC MATRIX COMPOSITE

L'invention concerne un procédé de fabrication d'une pièce en matériau composite comprenant un renfort fibreux et une matrice céramique présente dans la porosité du renfort fibreux, le procédé comprenant au moins les étapes suivantes : a) la formation du renfort fibreux par tissage tridimensionnel de fils céramiques (étape E1), le renfort fibreux ainsi formé présentant une armure interlock ; b) la formation d'une première phase de matrice céramique dans la porosité du renfort fibreux (étape E4) ; c) l'introduction dans la porosité du renfort fibreux, après mise en œuvre de l'étape b), d'une poudre comprenant des particules céramiques et/ou des particules de carbone (étape E5) ; et d) l'infiltration du renfort fibreux obtenu après mise en œuvre de l'étape c) par une composition d'infiltration à l'état fondu comprenant au moins du silicium de manière à former une deuxième phase de matrice céramique dans la porosité du renfort fibreux et obtenir ainsi la pièce en matériau composite (étape ...

ELEMENT OF TURBINE NOZZLE IN CMC, PROCEEDED FOR SA MANUFACTURE, AND DISTRIBUTOR AND GAS TURBINE INCORPORATING It.

METHOD OF OBTAINING BORAZANE

La présente invention a pour objet un procédé d'obtention du borazane (NH3-BH3). Le procédé comprend : - la mise à disposition d'un réacteur (1), équipé de moyens d'agitation et thermostaté entre une température θ1 et 40°C ; - l'introduction d'ammoniac liquide anhydre (NH3(I)) dans ledit réacteur (1) ; - l'introduction, avec agitation, dans ledit réacteur (1) renfermant l'ammoniac liquide anhydre (NH3(I), d'un complexe amine borane (Am.BH3), ledit complexe amine borane (Am.BH3), dont l'amine correspondante (Am) n'est soluble dans l'ammoniac liquide anhydre qu'à raison de moins de 10 g dans 100 g d'ammoniac à 20 °C, étant introduit en une quantité telle que le rapport molaire R = ammoniac liquide anhydre (NH3(I)) / complexe amine borane (Am.BH3) est supérieur ou égal à 5 ; - l'agitation du mélange ; - l'arrêt de l'agitation et l'obtention au sein dudit réacteur (1), de deux phases démixtées : + une phase légère (la) constituée essentiellement d'une solution d'ammoniac liquide anhydre (NH3 ...

PADDLE OF MATERIAL TURBOSHAFT ENGINE COMPOSITE AND PROCEEDED FOR SA MANUFACTURE.

Une aube de turbomachine en matériau composite comprenant un renfort fibreux densifié par une matrice est fabriquée par un procédé comprenant : - la réalisation par tissage tridimensionnel d'une ébauche fibreuse (100) en une seule pièce, - la mise en forme de l'ébauche fibreuse pour obtenir une préforme fibreuse en une seule pièce ayant une première partie formant préforme de pale et pied d'aube et au moins une deuxième partie formant préforme de plateforme ou talon d'aube, et - la densification de la préforme par une matrice pour obtenir une aube en matériau composite ayant un renfort fibreux constitué par la préforme et densifié par la matrice, et formant une seule pièce avec plateforme et/ou talon intégrés.

METHOD FOR CONTROLLING DISTRIBUTION WIRES A FIBROUS TEXTURE

La présente invention concerne un procédé de contrôle de la répartition des fils d'une texture fibreuse (4) comprenant au moins les étapes suivantes : - placement d'une texture fibreuse (4) dans une cavité de moulage (5) délimitée par un moule (2) et un contre-moule (3), le moule (2) et le contre-moule (3) étant chacun formés d'un matériau de densité dm vérifiant les deux conditions suivantes : dm ≤ 4 et |dm - dt| ≥ 0,1 où dt désigne la densité du matériau formant la texture fibreuse (4), - compactage de la texture fibreuse (4) entre le moule (2) et le contre-moule (3), et - réalisation d'une image à trois dimensions de l'intérieur de la texture fibreuse (4) ainsi compactée par tomographie aux rayons X afin de contrôler la répartition des fils de ladite texture fibreuse compactée. The present invention relates to a method for controlling the distribution of threads of a fibrous texture (4) comprising at least the following steps: - placing a fibrous texture (4) in a mold cavity (5) delimited by a mold (2) and a counter-mold (3), the mold (2) and the counter-mold (3) being each formed of a material of density dm satisfying the two following conditions: dm ≤ 4 and | dm - dt | ≥ 0.1 where dt denotes the density of the material forming the fibrous texture (4), - compacting the fibrous texture (4) between the mold (2) and the counter-mold (3), and - producing an image three-dimensional interior of the fibrous texture (4) and compacted by X-ray tomography to control the distribution of the son of said compacted fibrous texture.

METHOD OF MANUFACTURING A PART MADE OF A COMPOSITE BY SYNTHESIS BY REACTION SELF-SUSTAINING HIGH TEMPERATURE

L'invention concerne un procédé de fabrication d'une pièce en matériau composite à matrice céramique comportant l'étape suivante : a) fabrication de la pièce par formation d'une matrice céramique dans la porosité d'une structure fibreuse, la matrice céramique étant formée par synthèse par réaction auto-entretenue à haute température à partir d'une composition pulvérulente présente dans la porosité de la structure fibreuse. The invention relates to a method of manufacturing a piece of ceramic matrix composite material comprising the following step: a) manufacture of the part by forming a ceramic matrix in the porosity of a fibrous structure, the ceramic matrix being formed by high temperature self-sustained reaction synthesis from a powder composition present in the porosity of the fibrous structure.

SYNCHRONIZATION SYSTEM FOR NOZZLE FLAPS HAVING A VARIABLE CROSS SECTION

Un système de synchronisation entre un volet mobile interne et un volet mobile externe d'une tuyère à section variable (100) comprend un levier (130) fixé à un volet mobile interne et une biellette (140). La biellette comprend une tige (141) comportant à une extrémité une première tête (142) et à l'autre extrémité une deuxième tête (143), la première tête (142) étant reliée par un axe (151) au levier (130) tandis que la deuxième (143) tête est reliée au volet mobile externe. L'axe (151) reliant la première tête (142) de la biellette (140) au levier (130) comporte une portion conique (1513) maintenue par serrage dans un premier logement conique ménagé dans une chape (132) solidaire du levier (130). La portion conique (1513) présente un angle de cône supérieur à l'angle de cône du premier logement conique (1320).

RESISTANT MATERIALS AND PARTS HAS HIGH TEMPERATURE IN MEDIUM OXIDIZING AND THEIR MANUFACTORING PROCESS

Matériaux et pièces résistants à haute température en milieu oxydant et leur procédé de fabrication. Un matériau réfractaire résistant à haute température en milieu oxydant contient au moins: - un premier constituant correspondant à de l'hafnium, ou un composé non oxyde de l'hafnium, ou du zirconium ou un composé non oxyde du zirconium, ou correspondant à un mélange d'au moins deux métaux et/ou composés choisis parmi l'hafnium, un composé non oxyde de l'hafnium, du zirconium et un composé non oxyde du zirconium, - un deuxième constituant correspondant à du bore ou un composé non oxyde du bore, ou correspondant à un mélange de bore et d'un composé non oxyde du bore, - un troisième constituant correspondant à une terre rare RE ou un composé non oxyde de la terre rare RE, ou correspondant à un mélange de terre rare RE et d'un composé non oxyde de la terre rare RE, où RE est choisi parmi le scandium, l'yttrium et les lanthanides. Le matériau ne contient pas de silicium ni de composé du silicium ...

PROCESS FOR MANUFACTURING A PART MADE OF A CERAMIC MATRIX COMPOSITE

La présente invention concerne un procédé de fabrication d'une pièce en matériau composite à matrice céramique, le procédé comportant au moins l'étape suivante : - infiltration d'une préforme fibreuse avec une composition fondue comprenant majoritairement en masse du silicium, la préforme fibreuse comprenant des fibres de carbure de silicium, une poudre de carbure de silicium étant présente dans la porosité de ladite préforme, la taille moyenne des cristallites de carbure de silicium dans la poudre étant inférieure à la taille moyenne des cristallites de carbure de silicium dans les fibres, une matrice céramique étant formée dans la porosité de la préforme fibreuse durant l'infiltration afin d'obtenir la pièce en matériau composite.

THE OPTO-PYROTECHNIC INITIATOR

Un procédé de fabrication d'un initiateur opto-pyrotechnique (100) comprend les étapes suivantes : a) la formation d'un corps (110) comportant une cavité (111) dans laquelle une charge pyrotechnique (105) est destinée à être logée, le corps comportant en outre un passage interne (112) s'étendant entre une entrée (113) débouchant sur une face externe dudit corps et la cavité (111) renfermant la charge pyrotechnique (105), b) le placement d'une première portion (121) d'une fibre optique (120) dans le passage interne (112) du corps (110), une deuxième portion (122) de la fibre optique (120) s'étendant au-delà de l'entrée (113) du corps (110), une préforme de verre (140) étant interposée entre la fibre optique (120) et l'entrée (113) du corps (110), c) le traitement thermique de la préforme de verre (140) à une température supérieure au point de fusion de ladite préforme de verre de manière à former un élément de scellement hermétique en verre (150) entre la fibre optique (120) et l'entrée ...

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

Method for extracting solid soluble charges contained in a paste

The main subject of the present invention is a process for processing a paste (5) containing a solid charge (C) with a view to extracting at least one part of said solid charge (C). Said process comprises continuously: mixing, in a mixer (8), said paste (5) with a liquid solvent (3), a solvent for said at least one part of said solid charge (C), with a view to dissolving, at least partially, said at least one part of said solid charge (C) in said solvent (3); recovering, after said mixing, a biphasic system (15) comprising, on the one hand, a solution (3) enclosing at least one fraction of said at least one part of said solid charge (C), dissolved in said solvent (3), and on the other hand, a solid residue (5) of said paste (5); and then, separating said solution (3) and said solid residue (5) of said paste (5).

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.

SUSPENSIONS OF HEXANITROHEXAAZAISOWURTZITANE CRYSTALS, PRODUCTION OF SAID SUSPENSIONS AND PRODUCTION OF PYROTECHNIC OBJECTS

METHOD AND AUTONOMOUS PYROTECHNICAL DEVICE FOR INJECTING A FLUID

L'invention concerne un procédé et un dispositif (1Od) d'injection autonome d'un fluide (F) faisant intervenir des moyens pyrotechniques (1d). Ladite invention trouve notamment application dans un contexte d'injection d'un fluide (F) de sauvegarde dans un système susceptible de subir des échauffements (8d). De façon caractéristique, le procédé fait intervenir une charge thermo-initiable (1d).

PYROTECHNIC GRAINS OF LARGE DIMENSIONS, AND THEIR PRODUCTION AND USE

The present invention provides pyrotechnic grains of composition comprising at least one oxidizing charge and at least one reducing charge and no binder. In characteristic manner, said grains are in the form of substantially cylindrical blocks: with a thickness of more than 5 mm; with an equivalent diameter of 10 mm or more; and with porosity in the range 1% to 8%, limits included. Said grains, advantageously based on guanidine nitrate and basic copper nitrate, are suitable for the slow, low-pressure generation of gas over an extended period.

TURBOMACHINE BLADE HAVING COMPLEMENTARY EVEN/ODD GEOMETRY AND ITS MANUFACTURING METHOD

Turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, the blade including a first portion constituting an airfoil and a blade root. The first portion constitutes a single piece 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 piece 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.

METHOD OF MANUFACTURING A CMC FLOW MIXER LOBED STRUCTURE FOR A GAS TURBINE AEROENGINE

A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: .cndot. making a fiber preform (100) out of refractory fibers and having a shape corresponding to the shape of the lobed structure to be fabricated, from a plurality of component elements of fiber texture that are assembled together and shaped by means of tooling of a shape corresponding to the shape of the lobed structure to be fabricated so as to obtain an assembled fiber preform having a first preform portion (111) corresponding to the annular portion of the lobed structure and a second preform portion (112) corresponding to the multilobed skirt of the lobed structure, the component elements of the fiber preform being assembled together at least in part along connection lines (121) extending substantially in the flow direction of the flow past the lobes of the multilobed skirt preform portion; and ...

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.

PROCEDE DE FABRICATION D'UNE STRUCTURE ALVEOLAIRE DE FORME COURBEE EN MATERIAU COMPOSITE

Un procédé de fabrication d'une structure alvéolaire courbée comprend les étapes suivantes : - réalisation d'une structure fibreuse déployable (100) par tissage multicouche entre une pluralité de couches de fils de chaîne et une pluralité de couches de fils de trame, la structure fibreuse comportant des zones de déliaison s'étendant dans l'épaisseur de la structure fibreuse, les zones de déliaison étant espacées les unes des autres par des portions de liaison entre plusieurs couches de fils de trame, les portions de liaison étant décalées d'un ou plusieurs fils de trame dans une direction parallèle à celle des couches de fils de trame entre chaque série de plans d'armure, - imprégnation de la structure fibreuse (100) avec une résine précurseur d'un matériau déterminé, - déploiement de la structure fibreuse (100) sur un outillage de maintien (50) de manière à former dans la structure fibreuse une cellule ou alvéole au niveau de chaque zone de déliaison, l'outillage présentant en outre une ...

ENVIRONMENTAL BARRIER FOR A REFRACTORY SUBSTRATE CONTAINING SILICON

Une pièce comprenant un substrat (10), dont au moins une partie adjacente à une surface du substrat est en un matériau réfractaire contenant du silicium, est protégée par une barrière environnementale (20) formée sur la surface du substrat et ayant au moins une couche auto-cicatrisante (22) contenant un silicate de terre rare. La couche auto-cicatrisante (22) est formée: - pour au moins 90% molaire, d'un système constitué de 30% molaire à au plus 80% molaire d'au moins un silicate de terre rare RE2Si2O7, RE étant une terre rare, et d'au moins 20% molaire à 70% molaire d'oxyde de manganèse MnO, et - pour au plus 10% molaire d'un ou plusieurs oxydes à l'exception de MnO, ayant un point eutectique avec SiO2 inférieur ou égal à 1595°C, - la couche auto-cicatrisante (22) présentant une phase liquide ayant une fonction d'auto-cicatrisation dans au moins toute la plage de températures allant de 1200°C à 1400°C, tout en conservant une phase solide majoritaire.

ASSEMBLY HAVING A TEMPERATURE SELF-LOCKING CONNECTION

Un assemblage (100) comprenant une première pièce (10) et une deuxième pièce (20) en matériau composite maintenues l'une contre l'autre par au moins un système de fixation (50) comprenant une vis (30) comportant une tête fraisée (31) à partir de laquelle s'étend une partie filetée (32) et un écrou (40) comportant une tête fraisée (41) à partir de laquelle s'étend un fût (42) comportant un taraudage (43) coopérant avec la partie filetée (32) de la vis (30). La tête (31) de la vis (30) est en appui contre une fraisure (12) ménagée dans la première pièce (10). La tête de l'écrou (41) est en appui dans une fraisure (22) ménagée dans la deuxième pièce (20). Le système de fixation (50) est apte à faire basculer chaque tête (31 41) en direction de la fraisure (12; 22) dans laquelle elle est logée lors de la dilatation axiale du système de fixation (50).

LIGHTNING PROTECTION DEVICE AND METHOD OF PRODUCING SAME

L'invention concerne un dispositif de protection contre la foudre (200) destiné à être posé sur une structure (100) à protéger et comprenant : un premier revêtement comprenant au moins une couche de peinture conductrice (202), un deuxième revêtement (204) disposé sur le revêtement de surface et comprenant un matériau thermiquement isolant et électriquement conducteur.

FABRICATION PROCESS FOR DISTRIBUTOR SECTOR IN A TURBINE OR COMPRESSOR STATOR VANE OF A COMPOSITE MATERIAL FOR A TURBINE ENGINE AND TURBINE OR A COMPRESSOR INCORPORATING A DISTRIBUTOR OR A STATOR VANE MADE FROM SUCH SECTORS

Des aubes mono-pales ayant chacune une plate-forme intérieure (114), une plate-forme extérieure (116) et une pale (118) sont obtenues par réalisation par tissage tridimensioinnel d'une ébauche fibreuse en une seule pièce, mise en forme de l'ébauche pour obtenir une préforme fibreuse en une seule pièce, densification de la préforme par une matrice pour obtenir une aube en matériau composite formant une seule pièce avec plates-formes intérieure et extérieure intégrées. Plusieurs aubes sont assemblées et liées entre elles pour former un secteur multi-pales de distributeur de turbine ou de redresseur de compresseur en matériau composite.

COMPOSITE STRUCTURE THERMOSTRUCTURALE HAS GRADIENT OF COMPOSITION AND SONPROCEDE OF MANUFACTURE

THICKENING OF FIBROUS STRUCTURES BY RTM FOR THE REALIZATION OF COMPOSITE MATERIAL PARTS

PROCESS AND INSTALLATION OF DESTRUCTION OF ENGINES HAVE SOLID PROPELLANT

COMPOSITION SOLIDS GENERATORS Of HYDROGEN BY COMBUSTION INCLUDING/UNDERSTANDING UNBOROHYDRURE OF MAGNESIUM AND an OXIDANT OF the FAMILY OF the DINITRAMINES

SPACE PROPULSION MODULE-CHEMICAL AND SOLID PROPELLANT

METHOD FOR TREATING AQUEOUS MEDIA CONTAINING METAL NITRATE OR SULPHATE SALTS

NEW EQUIPMENT OF COOKING OF ENGINE HAS PROPELLANT SOLID AND PROCEEDED IMPLEMENTING IT

PYROTECHNIC COMPOSITIONS GENERATORS OF GAS, INCLUDING/UNDERSTANDING AMMONIUM NITRATE STABILIZES, COMPOSE PYROTECHNICAL CORRESPONDENTS

MANUFACTORING PROCESS Of a COMPOSITE MATERIAL PART THERMOSTRUCTURAL.

INSTALLING CHEMICAL VAPOR INFILTRATION HAS HIGH CHARGEABILITY

THREE-DIMENSIONAL FIBROUS REFRACTORY FIBRE STRUCTURE, PROCEEDED FOR SAREALISATION AND APPLICATION TO COMPOSITE MATERIALS THERMOSTRUCTURAUX

MATERIAL PART COMPOSITE THERMOSTRUCTURAL LOW THICKNESS AND MANUFACTORING PROCESS.

ROTARY ASSEMBLY FOR A TURBOMACHINE

PROPELLANTS HAS STRONG SPECIFIC IMPULSE COMPRISING OF DERIVED FROM THE FURAZANE

JACK HAS RACE DECLENCHEE PRESENTING OF the MEANS Of SEALING AND the MEANS OF BLOCKING OF the STEM

La présente invention concerne un vérin à course déclenchée (10), comportant un corps (12) abritant un ensemble mobile (18) comprenant un piston (20) et une tige (22), des moyens (24) pour propulser cet ensemble en réponse à une commande de déclenchement, des moyens de blocage de la tige (22) par rapport au corps de vérin (12), et un joint d'étanchéité (40) ménagé entre l'ensemble mobile (18) et le corps (12), et logé dans une première gorge annulaire (34) formée à la périphérie de l'ensemble mobile (18). Une seconde gorge annulaire (36) est ménagée sur la surface interne du corps de vérin (12), en regard de la première gorge (34), de sorte que le joint d'étanchéité (40) est logé partiellement dans la première gorge (34) et partiellement dans la seconde gorge (36) lorsque le vérin (10) se trouve dans une position non déclenchée, ce par quoi il forme les moyens de blocage de la tige (22 par rapport au corps de vérin (12).

PROCESS FOR MANUFACTURING A PART MADE CMC MATERIAL

ENVIRONMENTAL BARRIER FOR REFRACTORY SUBSTRATE CONTAINING OF SILICON

TURBOMACHINE BLADE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE COMPRISING SUCH A VANE

High pressure turbine shroud assembly for e.g. aeronautical gas turbine engine, has ring sector axially maintained by mutual engagement of groove and rib on supporting surfaces opposite to anchoring tab and flange of support structure

Un ensemble d'anneau de turbine comprend un anneau de turbine formé d'un ensemble de secteurs d'anneau (10) et une structure de support de l'anneau de turbine, chaque secteur d'anneau ayant une section sensiblement en forme de π avec une base annulaire (12) ayant une face interne du côté d'une veine d'écoulement de flux gazeux dans la turbine et une face externe à partir de laquelle font saillie deux pattes d'accrochage amont (14) et aval (16) ayant des extrémités maintenues en appui radial contre des surfaces de la structure de support. Chaque secteur d'anneau (10) est maintenu axialement par engagement mutuel de reliefs complémentaires (17, 37) sur des surfaces d'appui en regard d'une patte d'accrochage (16) et d'une partie (36) de la structure de support. Les secteurs d'anneau peuvent être en matériau composite à matrice céramique ...

METHOD FOR PRODUCING A RESIN ABLATIVE

La présente invention concerne un procédé de fabrication d'une résine ablative mettant en œuvre une réaction de réduction d'un composé de formule A suivie d'une réaction de polymérisation, la formule A étant la suivante : ...

Method for delivering hydrazine from container to rocket engine used for orbiting/de-orbiting e.g. satellite, involves generating pressurization gas by heating precursor liquid having saturating steam pressure greater than that of agent

La présente invention a pour objet un procédé de délivrance d'un agent liquide ou gélifié (8) à partir d'un réservoir (6) contenant ledit agent (8). Elle concerne également un dispositif (20) convenant à la mise en œuvre dudit procédé. Ledit procédé comprend la pressurisation, via un organe mobile imperméable (10), dudit agent (8) sous l'action d'un gaz de pressurisation (G), et il est caractérisé en ce que ledit gaz de pressurisation (G) est généré, au sein dudit réservoir (6), par chauffage d'un liquide précurseur (L) ; ledit liquide précurseur (L) ayant une pression de vapeur saturante supérieure à celle dudit agent (8) dans les conditions de température régnant au sein dudit réservoir (6).

DIFFUSER FOR EJECTOR INFLATION SYSTEM BY SUCTION

L'invention concerne un diffuseur (8) pour éjecteur de système de gonflage par aspiration, comprenant au moins une rampe annulaire de diffusion (16, 18) centrée sur un axe d'éjection (X-X) du diffuseur et destinée à être alimentée en gaz par un conduit d'alimentation (12), la rampe de diffusion présentant une section droite de forme cylindroconique , et une pluralité de tuyères d'éjection (20, 22) s'ouvrant dans la rampe de diffusion et régulièrement espacées autour de l'axe d'éjection du diffuseur, chaque tuyère d'éjection présentant une forme tronconique avec un axe longitudinal (Y-Y) qui est parallèle à l'axe d'éjection du diffuseur.

DEVICE OF LOADING FOR THE THICKENING BY CHEMICAL INFILTRATION IN VAPOUR PHASE IN FLOW DIRECTS POROUS SUBSTRATES OF THREE-DIMENSIONAL FORM

MANUFACTORING PROCESS OF COMPOSITE MATERIAL PARTS THERMOSTRUCTURAL

METHOD OF MAKING MATRIX COMPOSITE CARBIDE

PYROTECHNIC COMPOSITIONS NONTOXIC GENERATORS OF GAS HAS BASE DEPERCHLORATE Of AMMONIUM

PART COATED WITH A SURFACE COATING AND ASSOCIATED METHODS

L'invention concerne une pièce en matériau composite comportant un renfort fibreux densifié par une matrice céramique, la pièce présentant une surface externe et étant caractérisée en ce qu'elle est revêtue sur au moins une partie de sa surface externe par un revêtement de surface sous forme solide comportant un alliage de silicium et de nickel présentant une teneur massique en silicium comprise entre 29% et 45 % ou un alliage de silicium et de cobalt.

PROCESS FOR MAKING A FIBROUS STRUCTURE

L'invention concerne un procédé de fabrication d'une structure fibreuse, comportant les étapes suivantes : a) formation d'au moins une fibre céramique essentiellement amorphe par traitement thermique d'au moins une fibre précurseur de fibre céramique à une température comprise entre 900°C et 1200°C, et b) réalisation d'une ou plusieurs opérations textiles mettant en œuvre au moins une fibre céramique essentiellement amorphe formée lors de l'étape a) pour former une structure fibreuse comportant ladite au moins une fibre céramique essentiellement amorphe.

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

POLYMORPHIC FORM EPSILON Of a DRIFT OF the ISOWURTZITANE AND PROCESSES DESYNTHESE

TRIGGERED-STROKE ACTUATOR PROVIDED WITH A GAS DISCHARGE DEVICE

The invention relates to a triggered-stroke actuator () comprising a body () housing a piston () and a rod (), and a gas generator () mounted in said body () opposite said piston () and capable of pressurising a first chamber () defined between said gas generator and said piston, in which the piston () comprises, on its external face, a groove () in which is housed a sealing joint () with the body () of the actuator (). A calibrated passage (), adapted to evacuate gas from the first chamber (), is formed between the sealing joint () and the wall of the groove (). 1. A triggered-stroke actuator comprising a body housing a piston and a rod , and a gas generator mounted in said body opposite said piston and capable of pressurising a first chamber defined between said gas generator and said piston , in which the piston comprises on its external face a groove in which a sealing joint with said body is housed , characterised in that a calibrated passage adapted to evacuate gas from said first chamber is formed between the sealing joint and the wall of said groove.2. The actuator according to claim 1 , wherein the calibrated passage comprises at least one slot formed in the wall of the groove.3. The actuator according to claim 2 , wherein the slot is formed in the piston.4. The actuator according to claim 2 , wherein at least one wall part of the groove is formed by a split ring claim 2 , and in that the slot is formed by the slit of said split ring.5. The actuator according to claim 2 , wherein the groove has a bottom and two lateral walls extending respectively from an inlet of the groove to the bottom and from the bottom to an outlet of the groove and in that the slot comprises a segment formed in the bottom of the groove.6. The actuator according to claim 5 , wherein the slot also comprises a segment formed on at least one of the lateral walls of said groove.7. The actuator according to claim 2 , wherein the slot extends continuously over the entire internal contour of ...

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. 113-. (canceled)14. A refractory material withstanding high temperatures in an oxidizing medium , said material containing:{'sub': '2', '50% by volume HfB;'}25% by volume HfC; and{'sub': '2', '25% by volume TaB.'}15. A refractory part withstanding high temperatures in an oxidizing medium claim 14 , the part being wherein it is constituted by a refractory material according to .16. A part comprising a substrate made up of a determined material claim 14 , said part being provided with a protective coating for providing protection at high temperature in an oxidizing medium claim 14 , the part being wherein said protective coating is constituted by a refractory material according to .17. The part according to claim 16 , wherein the substrate is made of a monolithic ceramic material based on silicon carbide or of a monolithic material based on carbon claim 16 , or of a ceramic matrix composite material comprising silicon carbide.18. The part according to claim 16 , wherein the substrate is made of C/C composite material.19. The part according to claim 18 , further comprising a layer of silicon carbide close to the C/C composite material of the substrate of said part and a layer of zirconium carbide or of hafnium carbide interposed between the silicon carbide layer and the protective coating.20. A method of making a part out of refractory material withstanding high temperatures in an oxidizing medium claim 18 , the method comprising: [{'sub': '2', '50% by volume HfB;'}, '25% by volume HfC;', {'sub': '2', '25% by volume TaB; and'}], 'making a composition containingshaping the composition and densifying said composition.21. A method of making a protective layer that withstands high temperatures in an oxidizing medium on a part comprising a substrate made ...

Pyrotechnical actuator having pressure control means

LOW-THICKNESS THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND MANUFACTURE METHOD

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 ...

PROCESS FOR MANUFACTURING A PART MADE OF A CERAMIC MATRIX COMPOSITE CONTAINING MATRIX PHASES FOR HEALING AND DEFLECTING CRACKS

A method of fabricating a part of ceramic matrix composite material, the method comprises the steps of forming a porous fiber-reinforcing structure, introducing into the pores of the fiber structure powders containing elements for constituting the composite material matrix, forming at least a main fraction of the matrix from said powders by causing a reaction to take place between said powders; and the powders introduced into the fiber structure comprising elements that form at least one healing discontinuous matrix phase including a boron compound and at least one crack-deflecting discontinuous matrix phase including a compound of lamellar structure.

METHOD FOR SMOOTHING THE SURFACE OF A PART MADE FROM A CMC MATERIAL

A method of smoothing the surface of a ceramic matrix composite part presenting a surface that is undulating and rough. The method comprises forming a ceramic coating on the surface of the part, the coating being made by applying (20) a liquid composition on the surface of the part, the composition containing a ceramic-precursor polymer and a factory solid filler, curing the polymer (40), and transforming (50) the cured polymer into ceramic by heat treatment. The method further comprises impregnating (60) the ceramic coating with a liquid metallic composition.

FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC

An after-body assembly for an aeroengine, the assembly comprising an annular part (60) made of metallic material secured to the aeroengine and an after-body part (20) made of ceramic matrix composite material, the after-body part (20) being mounted on the annular part (60) by resiliently flexible fastener tabs (70) and having a first end (71) fastened to the annular part (60) and a second end (72) fastened to the upstream portion of the after-body part (20). Each fastener tab (70) includes an axial abutment element (720) that extends radially from the second end (72) of the tab and having at least a portion thereof facing the first end (71). The fastener tab (70) also includes a radial abutment element (721) at the second end (72) of the tab, the radial abutment element (721) at least partially overlying the first end (71).

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 () is placed in a chamber () situated between a vibration source () and a vibration sensor (), these elements being pressed towards each other by means () for applying initial mechanical loading. 1. A device for monitoring a viscoelastic material , comprising a sample-carrier in which there is defined a chamber for receiving a sample of said material , wherein the sample-carrier is shaped and dimensioned so as to be placed in the vicinity of a mass of material of the same kind as that which is placed in said chamber , wherein said chamber is provided with windows putting said sample into contact with the outside environment of said mass of material , and wherein the sample-carrier also includes a vibration source coupled to the wall of said chamber , a vibration sensor coupled to another wall of said chamber , and means for applying initial mechanical loading in order to press the two above-mentioned walls of said chamber against the sample , said vibration sensor being connected to calculation means in order to extract from the signal delivered by said sensor at least one parameter representative of the state of said sample.2. A device according to claim 1 , wherein the initial applied loading is less than 10 N.3. A device according to claim 2 , wherein the initial applied loading is less than or equal to 5 N.4. A device according to claim 1 , wherein said vibration source emits sinusoidal vibration at adjustable frequency.5. A device according to claim 4 , wherein an above-mentioned parameter is the loss factor of the material.6. A device according to claim 4 , wherein an above-mentioned parameter is the dynamic modulus of said material.7. A device according to claim 1 , wherein said sample chamber is defined by the two above-mentioned walls arranged parallel to each other claim 1 , ...

PROPULSION METHOD AND DEVICE COMPRISING A LIQUID OXIDANT AND A SOLID COMPOUND

One subject of the present invention is a propulsion method comprising: 2. The propulsion method as claimed in claim 1 , wherein said oxidizing charge is chosen from Sr(NO) claim 1 , ammonium dinitramide claim 1 , NHClO claim 1 , NHNOand mixtures thereof.3. The propulsion method as claimed in claim 1 , wherein the solid products generated claim 1 , together with said hydrogen (H) claim 1 , are injected into said combustion chamber then expelled from said combustion chamber with said combustion gases.4. The propulsion method as claimed in claim 1 , wherein said at least one liquid oxidizer (OX) is chosen from aqueous solutions of nitric acid claim 1 , hydrogen peroxide claim 1 , nitrogen peroxide claim 1 , hydroxylammonium nitrate claim 1 , ammonium dinitramide claim 1 , ammonium nitroformate and mixtures thereof.55. The propulsion method as claimed in claim 1 , wherein said at least one liquid oxidizer (OX) is a solution of hydrogen peroxide and wherein hydrogen (H) claim 1 , generated from said at least one solid compound (′) claim 1 , is generated from borazane claim 1 , combusted with an oxidizing charge.6. The propulsion method as claimed in claim 1 , which is carried out with thrust modulation.7. The propulsion method as claimed in claim 6 , wherein said thrust modulation is obtained by regulating the rate of injection of said at least one liquid oxidizer (OX) into said combustion chamber and/or the rate of injection of said hydrogen (H) claim 6 , generated from said at least one solid compound claim 6 , into said combustion chamber.9. The device as claimed in claim 8 , characterized in that said device for supplying said at least one combustion chamber with at least one liquid oxidizer (OX) comprises at least one pressurized tank that discharges via a valve.10. The device as claimed in claim 9 , wherein said at least one hydrogen generator is connected by means of a valve to said at least one tank so that the pressurization of said at least one tank is ...

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.

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. According to the invention, a pyrotechnically actuated gas generator ( 15 ) is arranged so as to emit gases resulting from the combustion of a charge, and the generator is associated with a variable configuration chamber ( 17 ) and a breakable conductive blade ( 19 ) constitutes a bottom partition of said chamber, the breaking of the blade under the influence of the gases bringing about the interruption of the electric circuit of which the blade is a part.

Fiber preform for a turbine ring sector, and its method of fabrication

A fiber preform for a turbine ring sector obtained by three-dimensional weaving and including a base-forming first portion, two tab-forming L-shaped portions each presenting two branches, two ends of the first portion being extended by respective ones of the first branches, and a second portion connecting together the two tabs, first and second strips woven together forming the first branches, a first fraction of the thicknesses of the second branches, and the first portion, there being a non-linked zone between them that is situated in the first branches and in the first portion, and a third woven strip forming the second portion and a second fraction of the thickness of the second branches of each of the tabs.

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. 1. A method for obtaining borazane , comprising the implementation of the successive stages below:a) obtention of a solution of borazane in a solvent consisting of tetrahydrofuran containing less than 100 ppm of water, advantageously less than 10 ppm of water; said borazane having been synthesized by reaction of at least one ammonium salt with at least one alkali and/or alkaline earth metal borohydride in said solvent or said borazane having been dissolved in said solvent, after having been synthesized by reaction of at least one ammonium salt with at least one alkali and/or alkaline earth metal borohydride in tetrahydrofuran containing less than 100 ppm of water, advantageously less than 10 ppm of water;b) precipitation of the borazane by addition to said solution of a non-solvent of borazane, containing less than 100 ppm of water, advantageously less than 10 ppm of water, and selected from the chlorinated solvents, fluorinated solvents, linear, branched and cyclic alkanes, and mixtures thereof;c) recovery, advantageously by filtration, of said precipitated borazane;d) possible drying of said recovered precipitated borazane.2. The method as claimed in claim 1 , which further comprises:e) hot dissolution, at a temperature lower than the decomposition temperature of the borazane, of said recovered ...

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. 1. An electric switch comprising:a hollow body defining a cavity;an actuator formed in said cavity;a slide mounted in said cavity downstream from said actuator and including at least one conductive portion; andat least two primary electrically-conductive studs forming a first pair, and a downstream electrically-conductive stud arranged downstream from said first pair,wherein said electrically-conductive studs are installed in the thickness of the hollow body and lead laterally into said cavity;wherein the conductive portion of the slide and the two primary electrically-conductive studs are electrically connected together when the slide is in a first position, thereby closing a first electric circuit; andwherein, under the action of the actuator, the slide is suitable for passing from its first position to a second position in which at least one primary electrically-conductive stud is no longer connected to the conductive portion of the slide, thereby opening the first electric circuit;said electric switch being characterized in that the conductive portion of the slide has a first projection situated upstream from the first primary electrically-conductive stud, and a second projection situated upstream from the downstream electrically-conductive stud, and in that when the slide is in its second position, the first and second projections are arranged to clamp ...

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: 2. The compound as claimed in claim 1 , wherein its composition consists of said guanidine nitrate claim 1 , potassium perchlorate claim 1 , at least one combustion modifier and optionally at least one additive.3. The compound as claimed in claim 1 , wherein its composition is at least 94% by weight claim 1 , advantageously at least 98% by weight claim 1 , or even 100% by weight claim 1 , made up of said guanidine nitrate claim 1 , potassium perchlorate and at least one combustion modifier.4. The compound as claimed claim 1 , wherein said at least one combustion modifier is chosen from zinc oxide (ZnO) claim 1 , iron oxide (FeO) claim 1 , chromium oxide (CrO) claim 1 , manganese dioxide (MnO) claim 1 , copper oxide (CuO) claim 1 , basic copper nitrate (Cu(NO).3Cu(OH)) and mixtures thereof.5. The compound as claimed in claim 1 , wherein said at least one combustion modifier consists of copper oxide and/or basic copper nitrate.6. The compound as claimed in claim 5 , which has a pressure exponent of less than or equal to 0.1 claim 5 , for a pressure of between 6 and 52 MPa.7. The compound as claimed in claim 1 , wherein said at least one combustion modifier has a specific surface area of greater than 3 m/g claim 1 , advantageously greater than 10 m/g and very advantageously greater than 25 m/g.8. The compound as claimed in claim 1 , wherein its composition contains silica as additive.9. The compound as claimed in claim 8 , wherein said silica is in pulverulent form having a high specific surface area claim 8 , advantageously of 100 m/g or more claim 8 , and of micrometric size claim 8 , advantageously of nanometric size claim 8 , or in the form of silica fibers of from 1 to 20 microns in diameter and from 20 to 500 microns in length.10. The compound as claimed in claim 1 , wherein it is obtained by means of a dry ...

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. 1. Support tooling for supporting at least one metal part that is to be subjected to heat treatment or shaped while hot , said tooling comprising: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; andat 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) being made of thermostructural composite material.2. Tooling according to claim 1 , including a plurality of pairs of jaws placed on either side of the metal part claim 1 , each jaw being slidably mounted on the support structure.3. Tooling according to claim 2 , wherein each jaw is provided with at least one guide each co-operating with a respective slideway formed in the support structure.4. Tooling according to claim 1 , wherein each jaw has an inside face for coming into contact with a portion of the metal part claim 1 , said face presenting a shape corresponding to the ...

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.

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. 115-. (canceled)16. A method of fabricating a turbine engine blade out of composite material comprising fiber reinforcement densified by a matrix , the method comprising:making a fiber blank by multilayer weaving a single piece comprising, in the longitudinal direction of said fiber blank corresponding to the longitudinal direction of the blade to be fabricated: a first set of a plurality of yarn layers that are interlinked to form a first portion of the blank corresponding to an airfoil preform; and a second set of one or more yarn layers that are interlinked at least locally to form at least a second portion of the blank corresponding to a blade root preform; the yarns of the first set of yarn layers not being interlinked with the yarns of the second set of yarn layers, the first set of yarn layers having the yarns of the second set of yarn layers crossing therethrough in the second portion of the blank;shaping the fiber blank to obtain a one-piece fiber preform having said first portion forming an airfoil preform and at least said second portion forming a blade root preform; anddensifying the preform with a matrix in order to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, forming a single piece incorporating a blade root.17. The method according to claim 16 , wherein the fiber blank is woven with a second continuous set of yarn layers claim 16 , and the shaping of the fiber ...

Method for the production of a curved ceramic sound attenuation panel

A method of fabricating a sound attenuation panel of curved shape, the method including impregnating a fiber structure defining a cellular structure with a ceramic precursor resin; polymerizing the ceramic precursor resin while holding the fiber structure on tooling presenting a curved shape corresponding to the final shape of the cellular structure; docking the cellular structure with first and second skins, each formed by a fiber structure impregnated with a ceramic precursor resin, each skin being docked to the cellular structure before or after polymerizing the resin of the skins; pyrolyzing the assembly constituted by the cellular structure and the first and second skins; and densifying the assembly by chemical vapor infiltration.

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. 110-. (canceled)11. A system for providing a vehicle with in-flight attitude control and side-force steering , the system comprising:a thruster body and a plurality of valves capable of generating side thrusts by being put into communication with the thruster body by means of a control device arranged to act individually on each valve;wherein the valves are distributed in first and second sets of valves, the two sets being disposed at a distance apart from each other respectively towards the front and towards the rear of the thruster body in a manner that is substantially symmetrical about the center of gravity of the vehicle, which center of gravity is situated on a longitudinal axis of the vehicle;wherein each set of valves is constituted by four valves and comprises a first pair of valves arranged to generate side thrust in opposite directions along thrust axes that are not aligned and are parallel to a first axis, and a second pair of valves that are arranged to generate side thrust in opposite thrust directions along thrust axes that are not aligned and are parallel to a second axis; andwherein the first and second axes ...

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. 1. A gas-generating pyrotechnic solid compound , the composition of which contains:guanidine nitrate,basic copper nitrate, andat least one inorganic titanate whose melting point is greater than 2100 K.2. The compound as claimed in claim 1 , wherein its composition contains at least one inorganic titanate chosen from metal titanates and alkaline-earth metal titanates claim 1 , and mixtures thereof.3. The compound as claimed in claim 1 , wherein its composition contains strontium titanate (SrTiO).4. The compound as claimed in claim 1 , wherein its composition contains calcium titanate (CaTiO).5. The compound as claimed in claim 1 , wherein its composition contains aluminum titanate (AlTiO).6. The compound as claimed in claim 1 , wherein its composition claim 1 , expressed as weight percentages claim 1 , contains between 1% and 5% of said at least one inorganic titanate.7. The compound as claimed in claim 1 , wherein its composition consists claim 1 , for at least 99.5% by weight claim 1 , of said guanidine nitrate claim 1 , basic copper nitrate and inorganic titanate(s).8. The compound as claimed in claim 1 , wherein its composition claim 1 , expressed as weight percentages claim 1 , contains:45% to 60% of guanidine nitrate,37% to 52% of basic copper nitrate, and1% to 5% of at least one inorganic titanate whose melting point is greater than 2100 K.9. The compound as claimed in claim 1 , wherein said at least one inorganic titanate has a median diameter of less than 5 μm.10. The compound as claimed in claim 1 , which is obtained via a dry-route process claim 1 , which comprises a step of compacting of a pulverulent mixture containing its constituent ingredients in ...

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. 1. A process for the production , self-regulated as a function of demand , of a gas (G) , said process being carried out under submerged conditions and comprising:the submersion in a liquid (L), capable of reacting with a solid (S) in order to produce said gas (G), of a reservoir containing a charge of said solid (S); said charge being arranged in the upper portion of the internal volume of said reservoir above a buffer volume free of any charge; said reservoir having in its bottom portion at least one opening suitable for the penetration of said liquid (L) into said free buffer volume and in its top portion at least one orifice suitable for discharging gas (G0, G);the penetration of said liquid (L) into said free buffer volume via said at least one opening and the rise in level of said liquid (L) in said internal volume of said reservoir with discharging of the gas initially present (G0) in said reservoir through said at least one orifice;the generation of gas (G) by reaction of said solid (S) in contact with said liquid (L), the rise of said gas (G) in said internal volume of said reservoir toward said at least one orifice and the discharging of said gas (G) via said at least one orifice; the level of said liquid (L) in said reservoir changing by itself as a function of the difference between the volume flow rate of gas generated and the volume flow rate of gas discharged via said at least one orifice.2. The process as claimed in claim 1 , which comprises the adjustment of the pressure of the ...

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. 112-. (canceled)13. 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 covering the bottom portion and the top portion of the annular loader space;each of the first and second annular vertical walls including support elements arranged in the annular loader space, the support elements of the first and second annular vertical walls being in radial alignment so as to define between them unit loader cells each for receiving a respective substrate to be densified; andthe device also including at least one gas feed orifice and at least one gas exhaust orifice in the vicinity of each unit loader cell.14 ...

Integrating after-body parts of an aeroengine

The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs.

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. 1. A pyrotechnic gas generator for driving an actuator , the generator comprising:a body defining a combustion chamber housing a main pyrotechnic charge;an ignitor for initiating combustion of said main pyrotechnic charge; andat least one delay chamber housing no pyrotechnic charge that is defined by walls that are stationary relative to one another and that is adapted to communicate with said combustion chamber via at least one inlet orifice,wherein said delay chamber is provided with at least one outlet orifice for passing gas out from said gas generator, said at least one outlet orifice being 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.2. The gas generator according to claim 1 , wherein the generator body is elongate in a main direction claim 1 , the combustion chamber and the delay chamber being arranged one after another inside said body in said main direction.3. The gas generator according to claim 1 , wherein the delay chamber is defined in the main direction by an upstream wall and by a downstream wall claim 1 , the inlet orifice being arranged in said upstream wall and the outlet orifice being arranged in said downstream wall.4. The gas generator according to claim 1 , wherein the body is cylindrical.5. The gas ...

METHOD FOR EXTRACTING SOLID SOLUBLE CHARGES CONTAINED IN A PASTE

The main subject of the present invention is a process for processing a paste () containing a solid charge (C) with a view to extracting at least one part of said solid charge (C). Said process comprises continuously: 1. A process for processing a paste containing a solid charge with a view to extracting at least one part of said solid charge , which comprises , continuously:mixing, in a mixer, said paste with a liquid solvent, which is a solvent for said at least one part of said solid charge, with a view to dissolving, at least partially, said at least one part of said solid charge in said solvent;recovering, after said mixing, a two-phase system comprising, on the one hand, a solution containing at least one fraction of said at least one part of said solid charge, dissolved in said solvent, and, on the other hand, a solid residue of said paste; and thenseparating said solution from said solid residue of said paste.2. The process as claimed in claim 1 , wherein said paste containing a solid charge has claim 1 , under the conditions for carrying out the mixing claim 1 , a viscosity of between 50 and 2000 Pa·s.3. The process as claimed in claim claim 1 , wherein said mixing is carried out in a static mixer.4. The process as claimed in claim 3 , wherein said paste and said solvent are introduced into said static mixer under pressure.5. The process as claimed in claim 1 , wherein said paste and said solvent are introduced separately or together claim 1 , after being brought into contact claim 1 , into said mixer.6. The process as claimed in claim 1 , which is carried out at ambient temperature or claim 1 , at least partially claim 1 , at a temperature above ambient temperature.7. The process as claimed in claim 1 , wherein the separation of said solution and of said solid residue is carried out by settling out.8. The process as claimed in claim 1 , which further comprises recovering said solution separated from said solid residue via an overflow.95. The process as ...

GAS-GENERATING PYROTECHNIC MONOLITHIC BLOCKS

A substantially cylindrical gas-generating pyrotechnical monolithic block has 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. 1. A gas-generating pyrotechnic monolithic block , of substantially cylindrical shape , wherein: an equivalent diameter greater than or equal to 10 mm, and', 'wherein', 'a porosity below 5%; and'}], 'the gas-generating pyrotechnic monolithic block has a thickness greater than or equal to 10 mm,'} +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 whose melting point is above 2100 K., 'a composition of the gas-generating pyrotechnic monolithic block, expressed in percentage by weight, contains, for at least 94% of its weight2. The block as claimed in claim 1 , whose thickness is between 10 and 100 mm and/or whose equivalent diameter is between 10 and 100 mm.3. The block as claimed in claim 1 , whose porosity is less than or equal to 2%.4. The block as claimed in claim 1 , wherein the composition of the gas-generating pyrotechnic monolithic block contains said guanidine nitrate and said basic copper nitrate in a ratio claim 1 , R claim 1 , between 8.5 and 15 (8.5≦R≦15).5. The block as claimed in claim 1 , wherein said at least one inorganic titanate consists of at least one inorganic titanate selected from the group consisting of metal titanates and alkaline-earth titanates.6. The block as claimed in claim 1 , wherein said at least one inorganic titanate consists of strontium titanate (SrTiO) and/or calcium titanate (CaTiO) and/or aluminum titanate (AlTiO).7. The block as claimed in claim 1 , wherein said guanidine nitrate claim 1 , ...

TRIGGERED-STROKE ACTUATOR WITH DAMPED RETURN TRAVEL

A triggered-stroke actuator presenting at least one additional pyrotechnic charge for adapting its resistance against return to vary in desired manner. 1. A triggered-stroke actuator comprising a body housing a piston connected to a rod that projects from one end of said body , said rod being adapted to be coupled to a mechanism able to exert thereon a variable return force , and a controlled gas generator mounted in said body facing said piston and at a predetermined distance from an initial position prior to being triggered , an expansion chamber thus being defined between said gas generator and said piston , said gas generator including an initial activation pyrotechnic charge of the actuator that is in communication with said expansion chamber , wherein the actuator further includes at least one additional pyrotechnic charge , situated in a housing in communication with the expansion chamber in order to exert resistance against return on the piston , which resistance is adapted to the way said variable return force acting on said rod varies over time.2. An actuator according to claim 1 , wherein said additional pyrotechnic charge presents a shape and/or a composition adapted so that its combustion generates a flow of gas in the expansion chamber at a rate that varies over time claim 1 , and that increases claim 1 , at least over a given period of time.3. An actuator according to claim 1 , wherein the additional pyrotechnic charge presents a varying section.4. An actuator according to claim 1 , wherein said additional pyrotechnic charge has a flared shape claim 1 , in particular a frustoconical or pyramid shape claim 1 , with its smaller section end being situated in the vicinity of said expansion chamber claim 1 , and in particular has a shape of axis that coincides with or is substantially parallel with the axis of the rod.5. An actuator according to claim 1 , wherein said additional pyrotechnic charge has a frustoconical shape of axis that coincides with the ...

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. 1. 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 comprising: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; andapplying 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.2. A method according to claim 1 , wherein clearance is provided between the inside wall of each perforation and the outside wall of the peg inserted in said perforation.3. A method according to claim 1 , wherein at least a first perforation is made in the assembly face of the first part and wherein a second perforation is made in the assembly face of the second part claim 1 , the ...

Low-thickness thermostructural composite material part, and manufacture method

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.

Method of treating ceramic fibers by phosphating

A method of treating silicon carbide fibers comprises phosphating heat treatment in a reactive gas so as to form a coating around each fiber for protection against oxidation. The coating comprises a surface layer of silicon pyrophosphate crystals and at least one underlying bilayer system comprising a layer of a phosphosilicate glass and a layer of microporous carbon.

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. 19-. (canceled)10. An assembly including at least one hollow part fastened on at least one structural part , wherein said assembly comprising at least one fastener device placed inside each hollow part , said fastener device comprising a one-piece body made of metal material presenting two main faces extending longitudinally between first and second ends of said body , each main face including a bearing portion in the vicinity of the first end of said body , each bearing portion including a fastener orifice for receiving a fastener member , the bearing portions being separated from each other by a slot extending from the first end of said body and over a determined depth within said body , the second end including at least one fastener orifice for receiving a fastener member , and wherein the two bearing portions of each fastener device are pressed against the inside surfaces of respective ones of the two walls of said hollow part by fastener members arranged in the fastener orifices of said bearing portions , the second end of the fastener device being fastened on the structural part by a fastener member arranged in the fastener orifice present in said second end.11. An assembly according to claim 10 , wherein the fastener orifices of the bearing portions are ...

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. 1. 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 bearing against a countersink formed in the first part , the head of the nut bearing against a countersink formed in the second part , the fastener system being suitable , during axial expansion of said fastener system , for causing at least one of the two heads to tilt towards the countersink in which it is housed.2. An assembly according to claim 1 , wherein at least one of the flat heads of the fastener system includes a plurality of radial slots and presents an angle (β; β) greater than the angle (α claim 1 , α) of the countersink of the part in which it is housed claim 1 , and wherein at least one head is held in prestress in said countersink.3. An assembly according to claim 2 , wherein the bolt and the nut are made of a material selected from at least one of the following materials: Inconel® 625 or 718 claim 2 , Waspaloy® claim 2 , Haynes® 282® claim 2 , A286 stainless steel claim 2 , and high-performance steel.4. An assembly ...

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 turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Method of locally treating a part made of porous composite material

A method of locally treating a portion of a part made of composite material including fiber reinforcement densified by a matrix, the material presenting internal pores, the method including: determining a quantity of infiltration composition as a function of a volume of the portion of the part to be treated, the infiltration composition including at least silicon; placing the determined quantity of infiltration composition in contact with pores opening out in a surface of the portion of the part to be treated; and applying heat treatment at a temperature higher than or equal to a melting temperature of the infiltration composition so as to impregnate the portion with the treatment composition and fill in the pores present in the portion.

Combined steering and drag-reduction device

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.

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. 1. A device for kneading a paste , the device comprising: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 at least one transport section carrying a main thread to cause the paste to advance along the two screws;an outlet orifice formed in a wall of the barrel to discharge the kneaded paste; anda holder device configured to hold each shaft at its second end, defining a downstream end, and enabling the shaft to rotate freely, the holder device comprising, for each shaft, a first portion secured to said shaft and a second portion secured to a cap end portion of the barrel, the cap end portion being removable and said first and second portions being configured to engage and disengage freely;wherein, for each shaft:the first portion of the holder device is a cylindrical sleeve fastened to the second end of said shaft, extending the shaft at least in part, and thus forming a cavity on the axis of said shaft;the second portion of the holder ...

PART MADE FROM OXIDE/OXIDE COMPOSITE MATERIAL FOR 3-D REINFORCING AND METHOD FOR MANUFACTURE OF SAME

A part made of oxide/oxide composite material includes fiber reinforcement constituted by a plurality of warp yarn layers and of weft yarn layers interlinked by three-dimensional weaving, with the spaces present between the reinforcing yarns being filled with a refractory oxide matrix. The fiber reinforcement presents a weave selected from the following weaves: interlock; multi-plain; multi-satin; and multi-serge, with warp and weft thread counts lying in the range 4 yarns/cm to 20 yarns/cm. The fiber reinforcement also presents a fiber volume fraction lying in the range 40% to 51%. 1. A part made of oxide/oxide composite material comprising fiber reinforcement constituted by a plurality of warp yarn layers and of weft yarn layers interlinked by three-dimensional weaving , with the spaces present between the reinforcing yarns being filled with a refractory oxide matrix;wherein the fiber reinforcement presents a weave selected from the following weaves: interlock; multi-plain; multi-satin; and multi-serge; and warp and weft thread counts lying in the range 4 yarns/cm to 20 yarns/cm, and wherein the fiber reinforcement presents a fiber volume fraction lying in the range 40% to 51%.2. A part according to claim 1 , wherein the part presents claim 1 , in monotonic traction claim 1 , at ambient temperature claim 1 , and in the warp direction:a modulus of elasticity lying in the range 120 GPa to 170 GPa;a breaking deformation of not less than 0.35%; anda breaking stress greater than 250 MPa.3. A part according to claim 1 , wherein the yarns of the fiber reinforcement are made of fibers constituted by one or more of the following materials: alumina; mullite; silica; an aluminosilicate; and a borosilicate.4. A part according to claims 1 , wherein the material of the matrix is selected from: alumina; mullite; silica; an aluminosilicate;and an aluminophosphate.5. A method of fabricating an oxide/oxide composite material part claims 1 , the method comprising the following steps ...

Manufactured and include the preparation method of turbine blade of the platform combined by composite

根据本发明，通过多层编织形成纤维坯料，所述纤维坯料具有对应于待制备的叶片的纵向方向的纵向方向，并在其厚度上包括具有纱的多个交织层的第一织造部分(102)、第二织造部分和第三织造部分。所述第一部分位于所述第二和第三部分之间，所述第一部分沿着其纵向维度的仅一部分与所述第二和第三部分交织。通过如下方式形成待制备的叶片的预成型体：在所述第一部分的两侧上展开不连结至所述第一部分的所述第二和第三部分的节段(104a、106a、104b、106b)，使所述第一部分成形以形成用于待制备的叶片的桨叶的预成型体部分，使所述第二和第三部分的经展开的节段成形以形成用于待制造的叶片的内部和外部平台的预成型体部分，用基体致密化所述叶片预成型体，以获得包括结合的平台的由复合材料制造的叶片。

Method for locally treating a part made from porous composite material

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.

Method for manufacturing a complexly shaped composite material part

本发明涉及一种复杂形状的复合材料部件，所述部件包括通过基质进行致密化的三维编织纤维增强件，并且通过包括如下步骤的方法进行制造：三维编织连续纤维带，所述连续纤维带包括一连串纤维坯料(200)，所述纤维坯料(200)构成具有待制造的具有多个部件的预成型件；接着将单个纤维坯料切割为带，每一个坯料(200)都由单个部件制成；对切割出的坯料进行成形，使得获得的纤维预成型件的形状对应于待制造部件的形状；使所述预成型件固结成预期形状；并且-通过化学气相渗透形成基质，从而对已固结预成型件进行致密化。

ONBOARD ELECTRICITY GENERATION SYSTEM WITH FUEL CELL

L'invention concerne un système de production d'électricité destiné à alimenter en énergie électrique un dispositif d'un aéronef. Ce système comprend un générateur (10) d'hydrogène gazeux à partir d'hydrogène sous forme non-gazeuse, un réservoir principal (30) connecté en son amont au générateur (10) et destiné à contenir de l'hydrogène gazeux sous une pression sensiblement supérieure à la pression atmosphérique, cet hydrogène gazeux étant produit par le générateur (10), au moins une pile à combustible (50), un détendeur (40) connecté en son amont au réservoir principal (30) et en son aval à la (ou les) pile à combustible (50), l'amont et l'aval étant définis par rapport au sens de circulation de l'hydrogène en conditions normales de fonctionnement du système, un dispositif de commande (70) qui régule le débit et la pression d'hydrogène gazeux du réservoir principal (30) vers la (ou les) pile à combustible (50) par l'intermédiaire du détendeur (40). The invention relates to an electricity generation system for supplying electrical energy to a device of an aircraft. This system comprises a generator (10) of gaseous hydrogen from hydrogen in non-gaseous form, a main tank (30) connected upstream to the generator (10) and intended to contain gaseous hydrogen under a pressure substantially greater than atmospheric pressure, this gaseous hydrogen being produced by the generator (10), at least one fuel cell (50), a pressure reducer (40) connected upstream to the main tank (30) and downstream to the (or the) fuel cell (50), the upstream and downstream being defined with respect to the direction of hydrogen circulation under normal operating conditions of the system, a control device (70) which regulates the flow and the pressure of hydrogen gas from the main tank (30) to the fuel cell (or cells) (50) via the pressure reducer (40).

METHOD FOR MANUFACTURING COMPOSITE MATERIAL

ROTARY ASSEMBLY FOR TURBOMACHINE

L'invention concerne un ensemble rotatif pour turbomachine, comprenant un disque dont la périphérie externe est formée d'une alternance d'alvéoles et de dents (12), et des aubes s'étendant radialement depuis le disque et dont les pieds (16) sont engagés axialement et retenus radialement dans les alvéoles du disque. Selon l'invention, les dents du disque et les pieds d'aube comprennent à leurs extrémités axiales amont et/ou aval des épaulements (74, 76) axiaux disposés circonférentiellement bout à bout en alternance et formant conjointement une surface cylindrique (78) faisant face radialement vers l'intérieur du disque. The invention relates to a rotary assembly for a turbomachine, comprising a disk whose outer periphery is formed of an alternation of cells and teeth (12), and blades extending radially from the disk and whose feet (16). are engaged axially and retained radially in the alveoli of the disk. According to the invention, the teeth of the disk and the blade roots comprise at their axial ends upstream and / or downstream axial shoulders (74, 76) circumferentially disposed end to end alternately and jointly forming a cylindrical surface (78) forming face radially towards the inside of the disc.

PYROTECHNIC PROCESS FOR PROVIDING VERY HIGH PURITY HYDROGEN AND ASSOCIATED DEVICE

FIRE EXTINGUISHER

La présente invention concerne un extincteur d'incendie (1) comprenant un corps (2) s'étendant le long d'un axe longitudinal (X) et définissant une chambre de stockage (4) dans laquelle un chargement d'un agent d'extinction est présent ainsi qu'une chambre de mise sous pression (5) comprenant un générateur de gaz pyrotechnique, la chambre de mise sous pression (5) étant séparée de la chambre de stockage (4) par une paroi perforée (7) configurée pour mettre en communication une sortie du générateur de gaz pyrotechnique avec la chambre de stockage (4), la paroi perforée (7) définissant un fond de la chambre de stockage (4), l'extincteur comprenant un canal d'évacuation configuré pour délivrer l'agent d'extinction à l'extérieur de l'extincteur (1) lors de l'actionnement du générateur de gaz pyrotechnique, ledit canal d'évacuation débouchant sur la chambre de stockage (4) au travers d'une ouverture (12a) positionnée à une distance de la paroi perforée (7), mesurée le long de l'axe longitudinal du corps, inférieure ou égale à la moitié de la longueur (ls) de la chambre de stockage (4). The present invention relates to a fire extinguisher (1) comprising a body (2) extending along a longitudinal axis (X) and defining a storage chamber (4) in which a loading of an agent of extinguishing is present as well as a pressurizing chamber (5) comprising a pyrotechnic gas generator, the pressurizing chamber (5) being separated from the storage chamber (4) by a perforated wall (7) configured to communicating an output of the pyrotechnic gas generator with the storage chamber (4), the perforated wall (7) defining a bottom of the storage chamber (4), the extinguisher comprising an evacuation channel configured to deliver the extinguishing agent outside the extinguisher (1) during the actuation of the pyrotechnic gas generator, said evacuation channel opening onto the storage chamber (4) through an opening (12a) positioned ...

PROCESS FOR OBTAINING BORAZANE

PROCESS FOR MANUFACTURING A PIECE OF MULTIPURPOSE COMPOSITE MATERIAL

Un procédé de fabrication d'une pièce en matériau composite multiperforée comprend les étapes suivantes : - positionnement d'un masque de sablage (250) sur une préforme (110) comprenant une texture fibreuse imprégnée avec une résine précurseur de céramique polymérisée, ledit masque comportant une pluralité d'ouvertures (251) correspondant aux perforations à réaliser dans la préforme (110), - projection de particules abrasives à grande vitesse sur la surface du masque (250) de manière à perforer la préforme (110) exposée dans les ouvertures dudit masque, - pyrolyse de la préforme multiperforée de manière à former une matrice céramique dans la texture fibreuse multiperforée. A method for manufacturing a multi-perforated composite material part comprises the following steps: positioning a sanding 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 on the surface of the mask (250) so as to perforate the preform (110) exposed in the openings of said mask, - pyrolysis of the multiperforated preform so as to form a ceramic matrix in the multiperforated fibrous texture.

OBTAINING A SOLID FORM COMPRISING BORAZANE STABILIZED THERMALLY THERE SOLID FORM AND ITS USE TO GENERATE HYDROGEN

METHOD OF MANUFACTURING A TURBOMACHINE VANE FROM COMPOSITE MATERIAL, THUS OBTAINED VANE AND TURBOMACHINE INCORPORATING IT

L'invention concerne un procédé de fabrication d'une aube de turbomachine en matériau composite à renfort fibreux densifié par une matrice et comprenant une pale, une plateforme située à une extrémité longitudinale de la pale et au moins un élément fonctionnel s'étendant à partir de la face externe de la plateforme. Le procédé comprend : - la réalisation par tissage multicouches d'une ébauche fibreuse en une seule pièce, - la mise en forme de l'ébauche fibreuse pour obtenir une préforme fibreuse en une seule pièce ayant une première partie (302) formant une préforme de la pale d'aube (320) et une deuxième partie (314) formant une préforme de la plateforme (340) et au moins une préforme d'élément fonctionnel (352 ; 354), et - la densification de la préforme fibreuse par une matrice. La deuxième partie de la préforme comprend un ensemble de couches de fils liées entre elles par tissage avec aménagement d'au moins une zone déliée permettant le déploiement de la préforme d'élément fonctionnel par rapport à la préforme de la première plateforme. The invention relates to a method for manufacturing a turbomachine blade made of composite material with fibrous reinforcement densified by a matrix and comprising a blade, a platform located at one longitudinal end of the blade and at least one functional element extending from from the outer face of the platform. The method comprises: - the production by multilayer weaving of a fibrous blank in a single piece, - the shaping of the fibrous blank to obtain a fibrous preform in a single piece having a first part (302) forming a preform of the blade blade (320) and a second part (314) forming a preform of the platform (340) and at least one functional element preform (352; 354), and - the densification of the fiber preform by a matrix . The second part of the preform comprises a set of layers of threads bonded together by weaving with arrangement of at least one untied zone allowing the ...

METHOD FOR MANUFACTURING ALVEOLAR STRUCTURE OF CURVED SHAPE IN COMPOSITE MATERIAL

EXPLOSIVE MASTERIZED BLOW EFFECT COMPOSITE

La présente invention a pour objet un explosif composite renfermant des charges énergétiques organiques dans un liant. De façon caractéristique : - ledit liant est un polyuréthane, obtenu par réticulation, via ses fonctions hydroxy terminales, d'un polybutadiène hydroxytéléchélique, avec au moins un agent de réticulation de type polyisocyanate ; ledit polybutadiène hydroxytéléchélique présentant une masse moléculaire moyenne en nombre (Mn) comprise entre 1800 et 3500 g.mol-1, avantageusement entre 2400 et 3500 g.mol-1 ; et - il renferme en outre des charges particulaires, dont le diamètre médian (d50) est inférieur ou égal à 300 µm ((d50 ≤ 300 µm) ; lesdites charges particulaires consistant : + d'une part, en des charges particulaires inertes denses, en un matériau présentant une densité supérieure à 5, convenant pour augmenter l'effet particulaire et limiter l'effet de souffle ; et + d'autre part, en des charges particulaires réductrices, convenant pour renforcer l'effet de souffle. The present invention relates to a composite explosive containing organic energy charges in a binder. Typically: said binder is a polyurethane, obtained by crosslinking, via its terminal hydroxy functions, of a hydroxytelechelic polybutadiene, with at least one crosslinking agent of polyisocyanate type; said hydroxytelechelic polybutadiene having a number average molecular weight (Mn) of between 1800 and 3500 gmol-1, preferably between 2400 and 3500 gmol-1; and it also contains particulate fillers whose median diameter (d50) is less than or equal to 300 μm ((d50 ≤ 300 μm), said particulate charges consisting of: + firstly, in dense inert particulate fillers, in a material having a density greater than 5, suitable for increasing the particle effect and limiting the blast effect, and + secondly, reducing particulate fillers, suitable for enhancing the blast effect.

DEVICE FOR SPRAYING A LIQUID

APPARATUS-FLAME DEVICE

Un dispositif accroche-flamme (100) pour canal de réchauffe d'un turboréacteur comprend un bras (120) en forme de goulotte délimitant une cavité (121) et un écran de protection thermique (130) fixé dans la cavité du bras. Le dispositif accroche-flamme (100) comprend en outre une platine de fixation (110) comportant un premier mât (114) intégralement formé avec la platine de fixation (110) et un deuxième mât (115) monté de façon amovible sur ladite platine, le bras (120) étant fixé aux premier et deuxième mâts (114, 115) par des organes de fixation.

STATOR SECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME

Un secteur (100) de stator de turbine comprend une pluralité de pales (110) en matériau composite comportant chacune un corps de pale (111) s'étendant entre des première et deuxième extrémités (112, 113). Le secteur comprend en outre des première et deuxième plateformes (120, 130) en matériau composite, la première plateforme (120) comprenant des ouvertures (121) dans lesquelles sont engagées les premières extrémités (112) de pales (110) et la deuxième plateforme (130) comprenant des ouvertures (131) dans lesquelles sont engagées les deuxièmes extrémités (113) de pales (110). Les ouvertures (121) de la première plateforme (120) présentent des dimensions supérieures aux dimensions des premières extrémités (112) des pales (110) engagées dans lesdites ouvertures (121) de manière à ménager un jeu (J) entre la première extrémité (112) de chaque pale (110) et l'ouverture (121). Chaque première extrémité (112) de pale engagée dans l'ouverture (121) présente des dimensions inférieures aux dimensions du corps de pale (111) de manière à définir un épaulement (1121) s'étendant autour de ladite première extrémité (112). L'épaulement présente des dimensions supérieures aux dimensions des ouvertures (121) de la première plateforme (120). A turbine stator sector (100) includes a plurality of composite material blades (110) each having a blade body (111) extending between first and second ends (112, 113). The sector further comprises first and second platforms (120, 130) of composite material, the first platform (120) comprising openings (121) in which are engaged the first ends (112) of blades (110) and the second platform (130) comprising openings (131) in which are engaged the second ends (113) of blades (110). The openings (121) of the first platform (120) have dimensions greater than the dimensions of the first ends (112) of the blades (110) engaged in said openings (121) so as to provide a clearance (J) between the first end ( 112) of each blade (110) and ...

METHOD OF BRAZING PARTS OF COMPOSITE MATERIAL WITH ANCHORING OF THE BRAZE JOINT

OPTIMIZED TRIM STRUCTURE FOR FLUID CONTACT COLUMN AND METHOD OF MANUFACTURE

La présente invention concerne une structure de garnissage formée par un agencement ordonné de faisceau de tubes (1). Pour chaque faisceau de tubes, les tubes (1) sont orientés selon les quatre directions formées par les diagonales d'un parallélépipède rectangle, qui possède une dimension supérieure aux autres.

WOVEN FIBROUS STRUCTURE HAVING SATIN WEAVING ON AT LEAST ONE OF ITS EXTERNAL FACES

La présente invention concerne une structure fibreuse tissée (1) présentant sur au moins une de ses faces externes (F1) un tissage à armure satin formé par liaison d'un premier ensemble de fils (T1S ; T1Z) avec un deuxième ensemble de fils (C1), caractérisée en ce que le premier ensemble de fils (T1S ; T1Z) est majoritaire sur la face externe, ledit premier ensemble de fils étant formé d'un mélange de fils (T1S) ayant une torsion S et de fils (T1Z) ayant une torsion Z. The present invention relates to a woven fibrous structure (1) having on at least one of its external faces (F1) a weave with satin weave formed by bonding a first set of threads (T1S; T1Z) with a second set of threads ( C1), characterized in that the first set of wires (T1S; T1Z) is predominant on the external face, said first set of wires being formed from a mixture of wires (T1S) having a twist S and of wires (T1Z) having a Z twist.

PROCESS FOR PRODUCING AN ABLATIVE RESIN

DEVICE FOR ASSISTING A SOLID PROPERGOL PROPULSIVE SYSTEM OF A MONOMOTING HELICOPTER, MONOMOTOR HELICOPTER COMPRISING SUCH DEVICE AND CORRESPONDING METHOD

L'invention concerne un dispositif d'assistance d'un système propulsif d'un hélicoptère monomoteur comprenant un moteur relié à une boîte (15) de transmission de puissance adaptée pour entraîner en rotation un rotor de l'hélicoptère, caractérisé en ce qu'il comprend : une turbine (18) d'entrainement en rotation d'un arbre (34) de sortie relié mécaniquement à ladite boite (15) de transmission de puissance ; et des moyens (16) commandés d'alimentation de ladite turbine (18) d'entrainement en fluide sous pression pour permettre à ladite turbine (18) de transformer l'énergie dudit fluide sous pression en énergie mécanique de rotation dudit arbre (34) de sortie. The invention relates to a device for assisting a propulsion system of a single-engined helicopter comprising a motor connected to a transmission transmission box (15) adapted to rotate a rotor of the helicopter, characterized in that it comprises: a turbine (18) rotational drive of an output shaft (34) mechanically connected to said transmission box (15); and means (16) for supplying said pressurized fluid drive turbine (18) to enable said turbine (18) to transform the energy of said pressurized fluid into rotational mechanical energy of said shaft (34) Release.

PROCESS FOR TREATING EFFLUENT GAS CONTAINING POLYCYCLIC AROMATIC HYDROCARBONS

La présente invention concerne un procédé de traitement de gaz effluent contenant des hydrocarbures aromatiques polycycliques comprenant une étape de lavage par pulvérisation d'une huile minérale afin de piéger lesdits hydrocarbures, caractérisé en ce que l'huile minérale comprend un mélange d'huile minérale aromatique et d'huile minérale naphténique. Elle comprend en outre l'utilisation d'une huile minérale naphténique pour abaisser la viscosité d'une huile minérale aromatique chargée en hydrocarbures aromatiques polycycliques, avantageusement d'une huile minérale aromatique contenant au plus 30% en volume d'hydrocarbures aromatiques polycycliques. The present invention relates to a process for treating effluent gas containing polycyclic aromatic hydrocarbons comprising a step of washing by spraying a 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. It further comprises the use of a naphthenic mineral oil for lowering the viscosity of an aromatic mineral oil loaded with polycyclic aromatic hydrocarbons, preferably an aromatic mineral oil containing at most 30% by volume of polycyclic aromatic hydrocarbons.

DEVICE FOR ATTACHING AUBES TO A TURBOMACHINE ROTOR DISC

ENSIME WIRE FOR SUBJECT TO TEXTILE OPERATION

L'invention concerne : Un fil (1) ensimé destiné à subir une opération textile comportant : une pluralité de fibres (2) céramiques et/ou de carbone, un revêtement d'interphase (3') recouvrant les fibres (2), et un film (4) recouvrant le revêtement d'interphase (3') comportant un polysiloxane à chaîne linéaire. The invention relates to: a sized yarn (1) intended to undergo a textile operation comprising: a plurality of ceramic and / or carbon fibers (2), an interphase coating (3 ') covering the fibers (2), and a film (4) covering the interphase coating (3 ') comprising a linear-chain polysiloxane.

METHOD OF MANUFACTURING A CURVED SHAPE ACOUSTICAL ATTENUATION PANEL

FLEXIBLE ANTI-CRUSHING FASTENING

Une Butée flexible (100) reliant une tuyère (220) et un corps (210) d'un propulseur (200) comprend un empilement de plusieurs armatures rigides (110a-110k) présentant une forme de tronc de sphère. Chaque armature rigide comporte un épaulement (111) sur une face et une gorge (112) sur la face opposée. L'épaulement (111) d'une armature est logé dans la gorge (112) de l'armature adjacente dans l'empilement. A flexible stop (100) connecting a nozzle (220) and a body (210) of a thruster (200) comprises a stack of several rigid armatures (110a-110k) having a shape of a truncated sphere. Each rigid armature has a shoulder (111) on one face and a groove (112) on the opposite face. The shoulder (111) of an armature is housed in the groove (112) of the adjacent armature in the stack.

ENVIRONMENTAL BARRIER FOR REFRACTORY SUBSTRATE CONTAINING SILICON

APPARATUS-FLAME DEVICE

COMPOSITE PYROTECHNIC PRODUCT WITH RETICULATED BINDER AND PROCESS FOR PREPARING THE SAME

La présente invention a pour objet un produit pyrotechnique composite, notamment une poudre propulsive pour armes à tube, renfermant des charges énergétiques organiques dans un liant réticulé. De façon caractéristique, la composition dudit produit, exprimée en pourcentages massiques, renferme : - de 78 à 90 %, avantageusement de 80 à 86 %, de charges énergétiques organiques, et - de 10 à 22 % d'un liant réticulé énergétique obtenu par réticulation, via seulement 8 à 12 % de ses fonctions azide, d'un polyazoture de glycidyle ayant une masse moléculaire moyenne en nombre comprise entre 700 et 3 000 g/mol, avec au moins un agent de réticulation renfermant au moins deux fonctions propargyle dans sa formule chimique, en présence d'au moins une gomme polymérique, choisie parmi les gommes polyuréthanne-polyester , les gommes polyuréthanne-polyéther et leurs mélanges, dont la masse moléculaire moyenne en nombre est supérieure à 20 000 g/mol et dont la viscosité Mooney est comprise entre 20 et 70 ML (5 +4) à 100°C ; ladite au moins une gomme polymérique représentant de 1 à 5 % en masse de la composition dudit produit pyrotechnique. Elle concerne également l'obtention desdits produits. Lesdits produits sont particulièrement intéressants de par leur propriétés et la simplicité de leur obtention.

PYROTECHNIC PROCESS FOR PROVIDING VERY HIGH PURITY HYDROGEN AND ASSOCIATED DEVICE

La présente invention a pour objet un procédé pyrotechnique de mise à disposition d'hydrogène de très grande pureté (G) ainsi qu'un dispositif (100) convenant à la mise en œuvre dudit procédé. Ledit procédé comprend : - la combustion d'au moins un chargement pyrotechnique solide générateur de gaz hydrogéné (4a, 4b, 4c, 4d) pour la production d'un gaz hydrogéné (G1), chaud, sous pression, renfermant au moins 70 % en volume d'hydrogène ; et - la purification d'au moins une partie dudit gaz hydrogéné sous pression (G1), par passage au travers d'une membrane métallique de séparation de l'hydrogène (9) maintenue à une température supérieure à 250°C, avantageusement entre 300 et 600°C, pour obtenir, au sortir de ladite membrane (9), un gaz hydrogéné (G) renfermant au moins 99,99 % en volume d'hydrogène. The subject of the present invention is a pyrotechnic method for providing very high purity hydrogen (G) as well as a device (100) suitable for implementing said method. Said method comprises: - the combustion of at least one solid pyrotechnic charge generating hydrogenated gas (4a, 4b, 4c, 4d) for the production of a hydrogenated gas (G1), hot, under pressure, containing at least 70% in volume of hydrogen; and purifying at least a portion of said hydrogenated gas under pressure (G1), by passing through a metal membrane for hydrogen separation (9) maintained at a temperature above 250 ° C., advantageously between 300 ° C. and 600 ° C, to obtain, at the exit of said membrane (9), a hydrogenated gas (G) containing at least 99.99% by volume of hydrogen.

DEVICE FOR GENERATING GASEOUS DIHYDROGEN

MIXING DEVICE PROVIDED WITH A TREE HOLDING DEVICE

Dispositif de malaxage d'une pâte permettant de malaxer et d'extruder une pâte de manière fiable et stabilisée, notamment pour la fabrication d'explosifs, et offrant un entretien facilité. Selon l'invention, ce dispositif de malaxage d'une pâte comprenant un fourreau oblong (10), deux arbres (14a, 14b), disposés parallèlement au sein du fourreau (10), maintenus et entraînés à leurs premières extrémités (15a, 15b), définissant l'amont (AM), par un dispositif d'entraînement (12), deux vis (20a, 20b) formée chacune par des filetages portés par les arbres (14a, 14b), chaque vis (20a, 20b) comportant au moins une section de transport (21a-21d) portant un filetage principal (21') pour faire progresser la pâte le long des deux vis (20a, 20b), et un orifice de sortie (19) pratiqué dans la paroi du fourreau (10) pour évacuer la pâte malaxée ; le dispositif de malaxage comprenant en outre un dispositif de maintien (30) configuré pour maintenir chaque arbre (14a, 14b) à sa seconde extrémité (16a, 16b), définissant l'aval (AV), et permettre sa libre rotation, ce dispositif de maintien (30) comprenant, pour chaque arbre (14a, 14b), une première partie (31) solidaire dudit arbre (14a, 14b) et une deuxième partie (36) solidaire d'une partie extrémale de capot (13) du fourreau (10), cette partie extrémale de capot (13) étant démontable et lesdites première (31) et deuxième (36) parties étant configurées pour s'engager et de se désengager librement. Device for kneading a dough for kneading and extruding a dough in a reliable and stabilized manner, in particular for the manufacture of explosives, and offering easy maintenance. According to the invention, this device for mixing a paste comprising an elongated sheath (10), two shafts (14a, 14b), arranged parallel to the sheath (10), held and driven at their first ends (15a, 15b). ), defining the upstream (AM), by a driving device (12), two screws (20a, 20b) each formed by threads carried by ...

PROCESS FOR MANUFACTURING COMPOSITE MATERIAL WITH CARBIDE MATRIX

Un procédé de densification d'un substrat poreux (50) par une matrice, ledit procédé comportant les étapes de : - fractionnement de la porosité présente dans le substrat poreux de manière à former dans ledit substrat un réseau de microporosités, ledit fractionnement étant réalisé avec une composition de comblement comprenant au moins une phase carbonée ou une phase carbure accessible via le réseau de microporosité, - infiltration chimique en voie gazeuse réactive du réseau de microporosités formé par le matériau de comblement, l'infiltration étant réalisée avec une composition gazeuse réactive dépourvue de carbone et comprenant au moins un élément apte à réagir avec le carbone de la composition de comblement pour former un carbure (53). A method of densifying a porous substrate (50) with a matrix, said method comprising the steps of: - fractionating the porosity present in the porous substrate so as to form in said substrate an array of microporosities, said fractionation being carried out with a filler composition comprising at least one carbon phase or a carbide phase accessible via the microporosity network, - chemical infiltration in the reactive gas route of the microporosity network formed by the filler material, the infiltration being carried out with a reactive gas composition devoid of of carbon and comprising at least one element capable of reacting with the carbon of the filler composition to form a carbide (53).

ROTARY ASSEMBLY FOR TURBOMACHINE

L'invention concerne un ensemble rotatif pour turbomachine, comprenant : - un disque (16) ayant une périphérie externe présentant une alternance d'alvéoles (22) et de dents (20), - des aubes (14) s'étendant radialement depuis le disque (16) et dont des pieds (24) sont engagés axialement et retenus radialement dans les alvéoles (22) du disque, - des plates-formes (30) s'étendant circonférentiellement depuis les aubes (14) et qui sont agencées circonférentiellement bout à bout, les unes vis-à-vis des autres, - des moyens d'étanchéité axiale amont et/ou aval d'une zone annulaire s'étendant radialement depuis les plates-formes (30) jusqu'au disque. Selon l'invention, les moyens d'étanchéité comprennent radialement une partie annulaire interne (64) et une partie annulaire externe (66) structurellement distinctes l'une de l'autre, et dont des extrémités radiales en vis-à-vis sont capables de déplacements radiaux relatifs par glissement de façon étanche, seule une reprise des efforts centrifuges de la partie externe (66) étant assurée en rotation par les plates-formes (30). The invention relates to a rotary assembly for a turbomachine, comprising: - a disc (16) having an outer periphery having an alternation of cells (22) and teeth (20), - blades (14) extending radially from the disc (16) and whose feet (24) are engaged axially and retained radially in the cavities (22) of the disk, - platforms (30) extending circumferentially from the blades (14) and which are arranged circumferentially end to each other, - axial sealing means upstream and / or downstream of an annular zone extending radially from the platforms (30) to the disk. According to the invention, the sealing means comprise radially an inner annular portion (64) and an outer annular portion (66) structurally distinct from one another, and radial ends facing each other are capable of radial relative displacements by sealingly sliding, only a recovery of the ...

DIFFUSER FOR EJECTOR OF INFLATION INFLATION SYSTEM

AUTOADHERENT ELASTOMERIC COMPOSITION

La présente invention concerne une composition élastomère réticulable comprenant un mélange (a) d'une composition élastomère à base d'un élastomère terpolymère éthylène-propylène-diène et (b) d'un copolymère amphiphile statistique ou à bloc d'un polymère hydrocarboné saturé ou insaturé en C2-C4 fonctionnalisé par un groupement fonctionnel polaire comprenant un groupement anhydride maléique. Elle concerne en outre la composition réticulée, son procédé de préparation et son utilisation en tant que protection thermique et/ou étanchéité interne d'un matériau composite et/ou pour accommoder les déformations mécaniques de ce matériau composite. Elle concerne de plus un assemblage comprenant (A) une structure en matériau composite et (B) une couche de revêtement en composition élastomère réticulée selon la présente invention, son procédé de préparation et son utilisation dans les domaines de l'aéronautique ou de l'aérospatial. The present invention relates to a crosslinkable elastomeric composition comprising a mixture (a) of an elastomer composition based on an ethylene-propylene-diene terpolymer elastomer and (b) a random or block amphiphilic copolymer of a saturated hydrocarbon polymer or C2-C4 unsaturated functionalized by a polar functional group comprising a maleic anhydride group. It also relates to the crosslinked composition, its method of preparation and its use as thermal protection and / or internal sealing of a composite material and / or to accommodate the mechanical deformations of this composite material. It further relates to an assembly comprising (A) a structure of composite material and (B) a coating layer of crosslinked elastomeric composition according to the present invention, its method of preparation and its use in the fields of aeronautics or the aerospace.

LOADING PROPERGOL, WITH MECHANICALLY REINFORCED LIEUR / PROPERGOL LINK AND PREPARATION

SHUTTER SYNCHRONIZATION SYSTEM FOR A VARIABLE SECTION TUBE

PROCESS FOR MANUFACTURING A CMC PIECE

SOLID COMPOUNDS, GENERATORS OF HYDROGEN BY SELF-MAINTAINED COMBUSTION, COMPRISING BORAZANE, AT LEAST ONE INORGANIC OXIDANT AND AT LEAST ONE METAL; PROCESS FOR GENERATING HYDROGEN

La présente invention a pour principal objet des composés solides aptes à générer de l'hydrogène selon une réaction de combustion auto-entretenue. Leur composition comprend du borazane, au moins un oxydant inorganique, et au moins un métal choisi parmi les métaux alcalino-terreux, l'aluminium, le titane et le manganèse ; lesdits borazane, au moins un oxydant inorganique et au moins un métal représentant au moins 95 % de la masse desdits composés. Elle concerne également la génération d'hydrogène par combustion auto-entretenue d'au moins un tel composé. The main subject of the present invention is solid compounds capable of generating hydrogen according to a self-sustaining combustion reaction. Their composition comprises borazane, at least one inorganic oxidant, and at least one metal selected from alkaline earth metals, aluminum, titanium and manganese; said borazane, at least one inorganic oxidant and at least one metal representing at least 95% of the mass of said compounds. It also relates to hydrogen generation by self-sustaining combustion of at least one such compound.

ASSEMBLY FOR EXTRACTING AT LEAST ONE MOLD SECTOR

PROCESS FOR PRODUCING ELECTRICITY BY A FUEL CELL; ASSOCIATED DEVICE

La présente invention a pour objet un procédé de production d'électricité (e) par une pile à combustible (1), comprenant successivement une phase de mise en régime de ladite pile (1), et un fonctionnement en régime stable de ladite pile (1), au cours duquel ladite pile (1), alimentée en un gaz hydrogéné (G'), produit de l'électricité (e) et de la chaleur. Selon ledit procédé, pour sa mise en régime, ladite pile (1) est alimentée en un gaz hydrogéné (G), renfermant au moins 70 % en volume d'hydrogène, généré par combustion auto-entretenue d'au moins un chargement pyrotechnique solide (A) générateur de gaz hydrogéné ; et durant son fonctionnement en régime stable, ladite pile (1) est alimentée en un gaz hydrogéné (G'), renfermant au moins 85 % en volume d'hydrogène, généré par décomposition thermique d'au moins un chargement solide (B) générateur de gaz hydrogéné ; une partie (qi) de la chaleur produite par ladite pile (1) en fonctionnement étant transférée audit au moins un chargement solide (B) pour le démarrage et l'entretien de sa décomposition thermique. La présente invention a également pour objet un dispositif convenant à la mise en œuvre dudit procédé. The subject of the present invention is a method for producing electricity (e) by a fuel cell (1), successively comprising a phase of ramping up said stack (1), and a steady-state operation of said stack ( 1), during which said battery (1) fed with a hydrogenated gas (G ') produces electricity (e) and heat. According to said method, for its operation, said stack (1) is fed with a hydrogenated gas (G), containing at least 70% by volume of hydrogen, generated by self-sustaining combustion of at least one solid pyrotechnic charge (A) hydrogenated gas generator; and during operation in a steady state, said battery (1) is fed with a hydrogenated gas (G '), containing at least 85% by volume of hydrogen, generated by thermal decomposition of at least one solid charge (B) ...

ENVIRONMENTAL BARRIER FOR REFRACTORY SUBSTRATE CONTAINING SILICON

Une pièce comprenant un substrat (10), dont au moins une partie adjacente à une surface du substrat est en un matériau réfractaire contenant du silicium, est protégée par une barrière environnementale (20) formée sur la surface du substrat et ayant au moins une couche auto-cicatrisante (22) contenant un silicate de terre rare. La couche autocicatrisante (22) est formée: - pour au moins 90% molaire, d'un système constitué de 30% molaire à au plus 80% molaire d'au moins un silicate de terre rare RE2Si2O7, RE étant une terre rare, et d'au moins 20% molaire à 70% molaire d'oxyde de manganèse MnO, et - pour au plus 10% molaire d'un ou plusieurs oxydes à l'exception de MnO, ayant un point eutectique avec SiO2 inférieur ou égal à 1595°C, - la couche auto-cicatrisante (22) présentant une phase liquide ayant une fonction d'auto-cicatrisation dans au moins toute la plage de températures allant de 1200°C à 1400°C, tout en conservant une phase solide majoritaire.

PYROTECHNIC GAS GENERATOR

Un générateur de gaz pyrotechnique (10) pour actionner un vérin (100), comprend un corps délimitant une chambre de combustion (12) abritant un chargement pyrotechnique principal (14), et un allumeur (16, 18) pour initier la combustion dudit chargement pyrotechnique principal (14). Le générateur de gaz pyrotechnique (10) comprend au moins une chambre de retardement (22) adaptée pour communiquer avec la chambre de combustion (12) par l'intermédiaire d'au moins un orifice d'entrée (62) et la chambre de retardement (22) est munie d'au moins un orifice de sortie (63) pour la passage des gaz hors dudit générateur de gaz, ledit au moins un orifice de sortie étant muni d'un opercule (73) adapté pour passer d'un état fermé à un état ouvert lorsque la pression à l'intérieur de la chambre de retardement atteint une pression limite de rupture (P1). A pyrotechnic gas generator (10) for actuating a cylinder (100) comprises a body defining a combustion chamber (12) housing a main pyrotechnic charge (14), and an igniter (16, 18) for initiating the combustion of said charge main pyrotechnic (14). The pyrotechnic gas generator (10) comprises at least one delay chamber (22) adapted to communicate with the combustion chamber (12) through at least one inlet port (62) and the delay chamber (22) is provided with at least one outlet orifice (63) for the passage of gases out of said gas generator, said at least one outlet orifice being provided with a lid (73) adapted to pass from a state closed in an open state when the pressure inside the delay chamber reaches a breaking pressure (P1).

METHOD FOR LASER CUTTING OF FIBROUS TEXTURE OF SILICON CARBIDE

L'invention concerne un procédé de découpe par laser d'une préforme fibreuse dans une texture fibreuse (10) obtenue par tissage de fils de carbure de silicium. Le procédé comprenant le placement de la texture fibreuse (10) sur un support (110) d'un outillage de découpe (100) et la découpe par un faisceau laser (141) du contour de la préforme fibreuse dans la texture fibreuse (10). Le support (110) de l'outillage de découpe (100) comporte une portion continument évidée (111) délimitant le contour de la préforme à découper, le faisceau laser (141) étant déplacé lors de la découpe de la texture fibreuse (10) suivant un chemin de découpe aligné sur la portion continument évidée (111) de manière à éviter un contact entre le faisceau laser (141) et le support (110). The invention relates to a method for laser cutting a fibrous preform into a fibrous texture (10) obtained by weaving silicon carbide threads. The method comprising placing the fibrous texture (10) on a support (110) of a cutting tool (100) and cutting by a laser beam (141) the contour of the fibrous preform into the fibrous texture (10) . The support (110) of the cutting tool (100) comprises a continuously recessed portion (111) delimiting the contour of the preform to be cut, the laser beam (141) being displaced during the cutting of the fibrous texture (10) following a cutting path aligned with the continuously recessed portion (111) so as to avoid contact between the laser beam (141) and the support (110).

TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET

CUTTING DEVICE INTENDED TO BE CONNECTED TO AN ELECTRICAL CIRCUIT

La présente invention concerne un dispositif de coupure (1) destiné à être relié à un circuit électrique comprenant au moins un initiateur pyrotechnique (3) et un corps (11) dans lequel sont présents : - une chambre de mise sous pression (7) en communication avec une sortie (S) dudit initiateur pyrotechnique (3), - au moins une portion conductrice de l'électricité (8) destinée à être reliée au circuit électrique, - au moins un élément fusible (40) relié en série à la portion conductrice, l'initiateur étant relié aux bornes dudit élément fusible et ledit élément fusible étant configuré pour se déclencher lorsque l'intensité du courant qui le traverse dépasse une valeur prédéterminée et pour actionner ainsi l'initiateur, et - un élément de coupure mobile (15), l'initiateur pyrotechnique étant configuré pour faire passer le dispositif de coupure d'une première configuration de passage du courant à une deuxième configuration de coupure du courant, l'élément de coupure mobile étant mis en mouvement lors du passage de la première à la deuxième configuration afin de déconnecter ladite portion conductrice. The present invention relates to a cut-off device (1) intended to be connected to an electrical circuit comprising at least one pyrotechnic initiator (3) and a body (11) in which are present: - a pressurizing chamber (7) in communication with an output (S) of said pyrotechnic initiator (3), - at least one electrically conductive portion (8) intended to be connected to the electrical circuit, - at least one fuse element (40) connected in series to the portion conductive, the initiator being connected to the terminals of said fuse element and said fuse element being configured to trip when the intensity of the current passing through it exceeds a predetermined value and thus to actuate the initiator, and - a movable cut-off element ( 15), the pyrotechnic initiator being configured to cause the cut-off device to pass from a first current flow ...

SURFACE COATING-COATED PIECE AND RELATED METHODS

PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE OF COMPOSITE MATERIAL

FIBROUS STRUCTURE FOR REINFORCING PIECES OF COMPOSITE MATERIAL WITH HIGH THICKNESS VARIATION

METHOD FOR SUPPLYING A MISSILE MOTOR TO A STORABLE ERGOL

La présente invention a pour objet un procédé d'alimentation d'un moteur de missile en un ergol stockable, comprenant les étapes successives ci-après : 1) la génération de gaz de combustion par combustion d'un chargement pyrotechnique, et la pressurisation dudit ergol stockable sous l'action desdits gaz de combustion, puis 2) la délivrance, à volonté, dudit ergol stockable pressurisé dans ledit moteur. De façon caractéristique, ledit procédé est mis en oeuvre avec un chargement pyrotechnique qui génère des gaz de combustion essentiellement constitués d'hydrogène. The present invention relates to a method for supplying a missile engine with a storable propellant, comprising the following successive steps: 1) the generation of combustion gases by combustion of a pyrotechnic charge, and the pressurization of said ergol storable under the action of said combustion gases, and 2) the delivery, at will, of said storable propellant pressurized in said engine. Typically, said process is carried out with a pyrotechnic charge which generates combustion gases consisting essentially of hydrogen.

METHOD FOR CONTROLLING A PIECE BY COLORIMETRY

RIGIDIFICATION OF THE CONNECTION BETWEEN SHUTTERS IN A VARIABLE SECTION TUBE

Une Tuyère à section variable (100) comprend un carter d'éjection (101) et une pluralité de volets internes (110) disposés en couronne en aval du carter d'éjection. Chaque volet interne est relié au carter d'éjection par un levier mobile (210 ; 220) monté de manière pivotante à l'extrémité aval (101a) du carter d'éjection (101). Chaque levier est mobile entre une première position dans laquelle les volets internes (110) sont en position haute et une deuxième position dans laquelle les volets internes sont en position braquée. La tuyère comprend en outre une pluralité de pièces rigides de transmission de mouvement (230) réparties de manière circonférentielle autour du carter d'éjection (101). Chaque pièce rigide de transmission de mouvement (230) est reliée à deux leviers adjacents (210, 220) par des bielles (240, 241). Chaque pièce rigide de transmission de mouvement est en outre reliée à un vérin de commande (250). Chaque pièce rigide de transmission de mouvement (230) peut se déplacer dans une direction (D230) correspondant à la direction axiale (XX') de la tuyère (100) sous l'action du vérin de commande (250) auquel il est relié de manière à déplacer les leviers adjacents entre les première et deuxième positions. A variable section nozzle (100) includes an ejection housing (101) and a plurality of inner flaps (110) disposed in a ring downstream of the ejection housing. Each inner liner is connected to the ejection housing by a movable lever (210; 220) pivotally mounted to the downstream end (101a) of the ejection housing (101). Each lever is movable between a first position in which the inner flaps (110) are in the up position and a second position in which the inner flaps are in the steered position. The nozzle further includes a plurality of rigid motion transmission pieces (230) circumferentially distributed around the ejection housing (101). Each rigid motion transmission part (230) is connected to two adjacent levers (210, 220 ...

PYROTECHNIC GAS GENERATOR

L'invention concerne un générateur de gaz pyrotechnique (10) comprenant un chargement pyrotechnique (30) comprenant un bloc en matériau pyrotechnique (32) traversé par un canal central (34), une chambre de combustion (20) abritant le chargement pyrotechnique (32), la chambre de combustion (20) étant délimitée par une paroi support (22) dans laquelle est formé un orifice de sortie (24) traversant pour le passage des gaz depuis la chambre de combustion (20) vers l'extérieur, et des moyens d'allumage (40) du chargement pyrotechnique. Selon l'invention, la chambre de combustion 20 abrite un filtre tubulaire (50) s'étendant selon une direction axiale (X1) et délimitant un conduit central (54) communiquant avec l'orifice de sortie (24). Le filtre (50) est ouvert radialement pour le passage des gaz, et le bloc en matériau pyrotechnique (32) est agencé pour entourer le filtre (50) de sorte qu'au moins une partie du filtre (50) est disposée dans le canal central (34) du bloc (32). The invention relates to a pyrotechnic gas generator (10) comprising a pyrotechnic charge (30) comprising a pyrotechnic material block (32) traversed by a central channel (34), a combustion chamber (20) housing the pyrotechnic charge (32). ), the combustion chamber (20) being delimited by a support wall (22) in which is formed an outlet orifice (24) extending for the passage of gases from the combustion chamber (20) to the outside, and ignition means (40) of the pyrotechnic charge. According to the invention, the combustion chamber 20 houses a tubular filter (50) extending in an axial direction (X1) and delimiting a central duct (54) communicating with the outlet orifice (24). The filter (50) is radially open for the passage of gases, and the block of pyrotechnic material (32) is arranged to surround the filter (50) so that at least a portion of the filter (50) is arranged in the channel central (34) of the block (32).

METHOD FOR SUPPLYING A MISSILE MOTOR TO A STORABLE ERGOL

PROCESS FOR MANUFACTURING A CMC PIECE

Une pièce en matériau composite à matrice au moins majoritairement en céramique est fabriquée par un procédé comprenant : la réalisation d'une préforme fibreuse à partir de fibres de carbure de silicium contenant moins de 1%at d'oxygène ; le dépôt sur les fibres de la préforme d'une interphase en nitrure de bore, le dépôt étant effectué par infiltration chimique en phase gazeuse avec une cinétique de dépôt inférieure à 0,3µm/h ; la réalisation d'un traitement thermique de stabilisation du nitrure de bore de l'interphase, après dépôt de l'interphase, sans exposition préalable de celle-ci à une atmosphère oxydante et avant dépôt de couche de matrice sur l'interphase, le traitement thermique étant réalisé à une température supérieure à 1300°C et au moins égale à la température maximale rencontrée ensuite jusqu'à achèvement de la densification de la préforme par la matrice ; et ensuite, la densification de la préforme par une matrice au moins majoritairement en céramique. A matrix material part at least predominantly made of ceramic material is manufactured by a process comprising: producing a fibrous preform from silicon carbide fibers containing less than 1% at oxygen; depositing on the fibers of the preform a boron nitride interphase, the deposition being carried out by chemical vapor infiltration with a deposition kinetics lower than 0.3 μm / h; performing a boron nitride stabilizing heat treatment of the interphase, after deposition of the interphase, without prior exposure thereof to an oxidizing atmosphere and before depositing a matrix layer on the interphase, the treatment thermal being performed at a temperature greater than 1300 ° C and at least equal to the maximum temperature subsequently encountered until completion of the densification of the preform by the matrix; and then, the densification of the preform with a matrix at least predominantly ceramic.

ROTARY ASSEMBLY FOR TURBOMACHINE WITH DEVICE FOR PLACING AUBES

L'invention concerne la mise en place d'aubes (54) sur un disque (12) de rotor d'une turbomachine. Un flasque annulaire amont (50) est disposé axialement en amont des aubes par rapport au sens de circulation de l'air dans la turbomachine, et présente des crochets (56) engagés avec un décrochement (58) formé en extrémité radialement interne des pieds d'aubes (52). The invention relates to the placement of vanes (54) on a rotor disc (12) of a turbomachine. An upstream annular flange (50) is disposed axially upstream of the blades with respect to the direction of air circulation in the turbomachine, and has hooks (56) engaged with a recess (58) formed at the radially inner end of the feet of the engine. blades (52).

METHOD FOR MANUFACTURING AN EXHAUST CASE OF COMPOSITE MATERIAL FOR A GAS TURBINE ENGINE AND AN EXHAUST CASE THUS OBTAINED

L'invention concerne un procédé de fabrication d'un carter d'échappement (10) en matériau composite pour moteur à turbine à gaz, le procédé comprenant la réalisation d'une virole externe (100) comprenant une plateforme (104) et une bride (106), la réalisation d'une virole interne (200) de diamètre inférieur à la virole externe et comprenant une plateforme (202) et une bride, la réalisation d'une pluralité de bras de carter (300) comprenant chacun une pale (302) se terminant à chaque extrémité radiale par une plateforme, l'aménagement dans la plateforme respective des viroles d'une pluralité d'ouvertures destinées chacune à recevoir une plateforme d'un bras de carter, et l'assemblage des bras de carter sur la virole externe et sur la virole interne en insérant les plateformes des bras de carter dans les ouvertures des viroles. L'invention a également pour objet un carter d'échappement en matériau composite obtenu par un tel procédé. The invention relates to a method for manufacturing an exhaust casing (10) made of a composite material for a gas turbine engine, the method comprising the production of an outer shell (100) comprising a platform (104) and a flange. (106), producing an inner ferrule (200) of smaller diameter than the outer ferrule and comprising a platform (202) and a flange, the embodiment of a plurality of crank arms (300) each comprising a blade ( 302) terminating at each radial end by a platform, arranging in the respective platform of the ferrules a plurality of openings each intended to receive a platform of a crank arm, and the assembly of the crank arms on the outer shell and on the inner shell by inserting the platforms of the casing arms in the openings of the ferrules. The invention also relates to an exhaust casing made of composite material obtained by such a method.

METHOD FOR DIAGNOSING LOADING

L'invention concerne un procédé de diagnostic d'un chargement (10) dans lequel on fournit le chargement (10) à contrôler équipé d'au moins un résonateur (26) fixé sur la surface (S) dudit chargement, on fait vibrer le résonateur (26), on identifie la fréquence de résonance du résonateur (26), et on en déduit de la fréquence de résonance au moins une valeur représentative de l'état mécanique du chargement (10). The invention relates to a method for diagnosing a load (10) in which the load (10) to be controlled, equipped with at least one resonator (26) fixed on the surface (S) of said load, is vibrated. resonator (26), the resonance frequency of the resonator (26) is identified, and at least one value representative of the mechanical state of the load (10) is deduced from the resonance frequency.

DIVERGENT COMPOSITE ROCKER MOTOR

TURBINE RING ASSEMBLY WITH AXIAL RETENTION

Un ensemble d'anneau de turbine comprend une pluralité de secteurs d'anneau (10) en matériau composite à matrice céramique formant un anneau de turbine (1) et une structure de support d'anneau (3) comportant deux brides annulaires (32, 36), chaque secteur d'anneau (10) ayant deux pattes (14, 16) maintenues respectivement entre les deux brides annulaires (32, 36) de la structure de support d'anneau (3). Les deux brides annulaires (32, 36) de la structure de support d'anneau (3) exercent une contrainte sur les pattes (14, 16) des secteurs d'anneau (10). Une (36) des brides de la structure de support d'anneau (3) est élastiquement déformable dans la direction axiale (DA) de l'anneau de turbine (1). A turbine ring assembly includes a plurality of ceramic matrix composite ring forming sectors (10) forming a turbine ring (1) and a ring supporting structure (3) having two annular flanges (32, 36), each ring sector (10) having two tabs (14, 16) held respectively between the two annular flanges (32, 36) of the ring support structure (3). The two annular flanges (32, 36) of the ring support structure (3) stress the tabs (14, 16) of the ring sectors (10). One (36) of the flanges of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1).