Abrégé

L'invention concerne un absorbant acoustique (100) s'étendant entre deux surfaces opposées (100a,100b) et combinant un ou plusieurs résonateurs acoustiques quart-d'onde (102,102') avec un élément microporeux (101). Chaque résonateur acoustique (102, 102') a une longueur L, sensiblement supérieure à une épaisseur t de l'absorbant acoustique (100), entre une première extrémité (102a) ouverte sur une première surface (100a) des deux surfaces opposées (100a,100b) de l'absorbant acoustique (100), et une deuxième extrémité (102b) fermée. L'élément microporeux (101) est constitué d'une pluralité de cellules unitaires périodiquement répétées et adjacent aux résonateurs acoustiques (102), (102'). L'invention concerne aussi un procédé de production de cet absorbant acoustique, comprenant au moins une étape de fabrication additive.

Classes IPC  ?

• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
• B33Y 10/00 - Procédés de fabrication additive
• F02C 7/24 - Isolation thermique ou acoustique

Abrégé

Disclosed is a structure (50) for linking and supporting a turbine engine (10) on an aircraft pylon (32), the structure (50) having a first longitudinal axis (C) intended to extend parallel to a second longitudinal axis (B) of the pylon (32), the structure (50) comprising: -a first axial portion (50a) for fastening to the pylon (32), said first portion (50a) having an upper end that defines a substantially horizontal plane (P3) of interface with the pylon (32), and a lower end bearing suspension rods (62, 64) for suspending the turbine engine (10), which extend in a rear vertical plane (P2); and -a second axial portion (50b) that is intended to extend forward of the pylon (32) and comprises at least one suspension member (66) of the turbine engine (10) in a front vertical plane (P1).

Classes IPC  ?

• B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
• B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
• B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci

Abrégé

L'invention concerne le domaine des méta-matériaux acoustiques et en particulier un procédé de fabrication d'un méta-matériau acoustique (100) comportant une pluralité de colonnes (101) s'étendant à partir d'une base commune, ainsi que le méta-matériau acoustique (100) obtenu par ce procédé. Ce procédé comprend une étape fabrication additive d'un moule (210) par dépôt d'une pluralité de strates empilés (203) comprenant chacun une pluralité de cellules (204) périodiquement répétées, séparées par des parois (205), les cellules (204) de la pluralité de strates empilés (203) étant alignées de manière à former des canaux (206), une étape de remplissage des canaux (206) avec un matériau fluide (220), une étape de solidification du matériau fluide (220), et une étape d'élimination du moule (210).

Classes IPC  ?

• B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p.ex. modélisation par dépôt de fil en fusion [FDM]
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• B29C 39/10 - Moulage par coulée, c. à d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulage; Appareils à cet effet pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés en incorporant des parties ou des couches préformées, p.ex. coulée autour d'inserts ou sur des objets à recouvrir

Abrégé

L'invention concerne un méta-matériau acoustiques (100), ainsi qu'un procédé pour sa fabrication. Le méta-matériau acoustique comprend une pluralité de canaux (101) ayant chacun une même section transversale avec un rayon hydraulique entre 5 et 300 pm, disposés avec un espacement périodique (t) entre canaux adjacents entre 2 et 600 pm. On peut ainsi obtenir un réseau hautement dense de micro-canaux acoustiques pouvant offrir une absorption et/ou impédance acoustiques optimales sur une large bande de fréquences. Son procédé de fabrication est un procédé de fabrication additive comprenant plusieurs étapes consécutives de dépôt de matériau pour former, dans chaque étape, une couche (203) comportant une pluralité de cellules (204) périodiquement répétées, séparées par des parois (104). Les couches (203) déposées dans les étapes consécutives de dépôt de matériau sont empilées avec leurs cellules (204) respectives alignées de manière à former les canaux (101).

Classes IPC  ?

• G10K 11/175 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets d'interférence; Masquage du son
• B64C 1/40 - Insonorisation ou isolation calorifique
• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
• G10K 11/162 - Sélection de matériaux

Abrégé

Said method for determining aircraft landing runway conditions comprises the steps of: acquiring a set of data groups of different types (D1, D2) for evaluating and monitoring runway degradation conditions; deriving weighting coefficients (Ki) from each data group; filtering the data; determining, for each data group, a partial runway condition; modifying the weighting coefficients of each data group; and combining the partial runway conditions to derive a runway condition coefficient (RWYCC) associated with a confidence index (CI) derived from the modified weighting coefficients.

Classes IPC  ?

• G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage

Abrégé

Procédé (100) de fabrication d'un matériau poreux multicouches par fabrication additive (104), ledit matériau comprenant au moins deux couches superposées homogènes formées par des filaments, caractérisée en ce que le procédé de fabrication comprend un procédé de détermination de caractéristiques géométriques de chaque couche du matériau qui comprend les étapes suivantes : - détermination (101) des paramètres JCAL d'un modèle de fluide équivalent de différentes couches homogènes formées de filaments en fonction des paramètres microstructuraux des couches ; - détermination (102) du comportement acoustique d'un matériau poreux multicouches comprenant au moins deux couches homogènes superposées formées de filaments à partir des épaisseurs desdites couches et des paramètres JCAL déterminés précédemment ; et - détermination (103) de l'épaisseur et des paramètres microstructuraux des couches du matériau poreux multicouches de manière à ce qu'au moins une grandeur parmi une impédance acoustique, un coefficient d'absorption ou de réflexion du matériau poreux soit comprise dans un intervalle ciblé selon une fréquence acoustique.

Classes IPC  ?

• B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
• B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• B32B 7/022 - Propriétés mécaniques
• B32B 5/08 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments les fibres ou filaments d'une couche étant disposés d'une certaine manière ou étant faits de substances différentes
• B32B 37/00 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons
• F02C 7/24 - Isolation thermique ou acoustique

Abrégé

Revêtement de traitement acoustique comprenant un métamatériau (201), caractérisé en ce que le métamatériau comprend une structure solide (210) comprenant au moins un espace libre (211, 212, 213) formant une cavité repliée et au moins un matériau poreux placé dans ledit espace libre de la structure solide.

Classes IPC  ?

• G10K 11/175 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets d'interférence; Masquage du son
• G10K 11/162 - Sélection de matériaux

Abrégé

The invention relates to a tool (22) for removing a fan disc from a module of a turbine engine comprising a rotor and a stator, the rotor comprising the fan disc, a drum and a sealing part secured to one another via bolts each comprising a screw and a nut, each screw passing through a retaining member having at least two lugs arranged around a head of the screw, the stator being delimited by a straightener having a flange, the tool (22) comprising: - a frame (23); - a plate (25) comprising pins and two holes, each of the pins being configured to support the head of a screw, each hole being configured to receive an indexing finger; - at least three supports (30) comprising bearing surfaces (31) configured to support the flange of the straightener; - a visual marker (32) configured to angularly orient the module with respect to the tool (22).

Classes IPC  ?

• F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
• B23P 19/04 - Machines effectuant simplement l'assemblage ou la séparation de pièces ou d'objets métalliques entre eux ou des pièces métalliques avec des pièces non métalliques, que cela entraîne ou non une certaine déformation; Outils ou dispositifs à cet effet dans la mesure où ils ne sont pas prévus dans d'autres classes pour assembler ou séparer des pièces

Abrégé

A discharge grid (22) designed to be mounted inside or at the outlet of a line (21) of a discharge valve (20) of a turbomachine (1) of an aircraft, the discharge grid (22) comprising an upstream face (24) designed to receive a gas flow (F), a downstream face (25) parallel to the upstream face (24) and designed to deliver the gas flow (F) received at the upstream face (24), and orifices (230) passing through the perforated plate (23) from the upstream face (24) to the downstream face (25) and designed to convey the gas flow (F) through the perforated plate (23). The discharge grid (22) comprises, for each orifice (230) of the perforated plate (23), a tubular channel (26) that is coaxial with its associated orifice and projects from the downstream face (25) of the perforated plate (23).

Classes IPC  ?

• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F01D 17/10 - Organes de commande terminaux
• F02K 3/075 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux commande du rapport des débits des différents flux

Abrégé

An acoustic treatment grid (22) designed to be mounted inside or at the outlet of a line (21) of a discharge valve (20) of a turbomachine (1) of an aircraft, this being designed to convey a gaseous flow (F), the grid (22) comprising a perforated plate (23) and circular orifices (230) passing through the perforated plate (23) in a first direction (DA), the orifices (230) having a diameter (D) and a geometric center (C). Each orifice (230) is separated from an adjacent orifice by a space whose length (e) is equal to the product of the diameter (D) of said orifice (230) with a spacing coefficient whose value is between 1.1 and 6.

Classes IPC  ?

• F02C 7/24 - Isolation thermique ou acoustique
• F01D 17/10 - Organes de commande terminaux
• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F02K 3/075 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux commande du rapport des débits des différents flux
• F04D 29/52 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes axiales
• F04D 29/66 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analogues; Equilibrage

Abrégé

One aspect of the invention relates to a method for controlling a turbojet thrust reverser during an aborted aircraft takeoff, the thrust reverser comprising: - doors that can move between a closed position, an over-closed position and a deployed position; - door actuators configured to move the doors between the closed, over-closed and deployed positions; - a device for locking the doors in the closed position, said device being movable between a locking position and an unlocking position; and - a lock actuator configured to move the locking device between the locking and unlocking positions. The method comprises the following steps: - reducing the engine speed of the turbojet by following a setpoint value below a first engine speed threshold value at which the aerodynamic forces exerted on the doors are equal to the forces developed by the door actuators; - controlling the door actuators in such a way as to bring the doors into the over-closed position; - controlling the lock actuator in such a way as to bring the locking device into the unlocking position; and - when the locking device is in the unlocking position, controlling the door actuators in such a way as to bring the doors into the deployed position; - in which method the setpoint value of the engine speed is above the idle speed.

Classes IPC  ?

• F02K 1/76 - Commande ou régulation des inverseurs de poussée
• F01D 21/14 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à d'autres conditions spécifiques

Abrégé

Abrégé Procédé de fabrication d'une pièce en matériau composite L'invention concerne un procédé de fabrication d'une pièce en matériau composite à matrice organique ayant une porosité réduite. Figure pour l'abrégé : Fig. 5. CA 3070727 2020-01-30

Classes IPC  ?

• C08J 5/24 - Imprégnation de matériaux avec des prépolymères pouvant être polymérisés en place, p.ex. fabrication des "prepregs"
• C08K 3/013 - Charges, pigments ou agents de renforcement
• C08K 7/04 - Fibres ou "whiskers" inorganiques

Abrégé

The invention relates to an assembly (1) for a turbine engine extending along an axis, comprising a stator, a low-pressure compressor shaft (4), a low-pressure compressor comprising a rotor comprising a drum (2) rotatably coupled to the shaft (4) of the low-pressure compressor, a fan (21) comprising a disk (23) rotatably coupled to the shaft (4) of the low-pressure compressor, characterised in that the drum (2) comprises a radially internal part (3) rotatably coupled to the shaft (4) of the low-pressure compressor and a radially external part (5) fixed to the radially internal part (3) by means of detachable fixing means (11), first axial retention means (30) capable of axially and detachably retaining the disk (23) of the fan (21) relative to the shaft (4) of the low-pressure compressor, second axial retention means (15) capable of axially and detachably retaining the radially internal part (3) of the drum (3) relative to the shaft (4) of the low-pressure compressor.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p.ex. rotors
• F01D 5/06 - Rotors à plus d'un étage axial, p.ex. du type à tambour ou à disques multiples; Leurs parties constitutives, p.ex. arbres, connections des arbres
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
• F04D 29/054 - Dispositions pour le raccordement ou l'assemblage des arbres
• F04D 29/26 - Rotors spécialement adaptés aux fluides compressibles

Abrégé

A system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means (52) configured to activate the thrust reversal means when the first detection means (31) detects a condition for activation of the thrust reversal means. It further comprises a second detection means (42, 44, 46, 48, 49) configured to detect a condition for activation of the reverse idle control, the control means (38) being configured to activate the reverse idle control when the second detection means (42, 44, 46, 48, 49) detects a condition for activating the reverse idle control.

Classes IPC  ?

• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
• F02K 1/76 - Commande ou régulation des inverseurs de poussée

Abrégé

Disclosed is a compressor (1) of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor (1) comprising a low-pressure compressor, a high-pressure compressor (3) and an intermediate casing (2) axially connecting the low-pressure compressor and the high-pressure compressor (3), the high-pressure compressor (3) comprising an inlet guide stator (33) comprising a retaining ring (34), an outer high-pressure compressor casing (35) and a plurality of vanes (38), the compressor (1) comprising an immobilising device (5) comprising at least one first member secured to the intermediate casing (2) and at least one second member secured to the retaining ring (34) and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring (34) relative to the intermediate casing (2) according to the axis X.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations

Abrégé

The invention relates to a turbomachine moving blade (2) comprising at least one cooling circuit comprising at least one cavity (16; 16a, 16b) extending radially between the foot and the vertex, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots (18) arranged to open out along the trailing edge between the foot and the vertex, and a plurality of second discharge slots (20) which are separate from the first discharge slots and provided along the trailing edge (14) between the foot and the vertex, the second discharge slots (20) being axially offset upstream from the first discharge slots (18) and each of the first discharge slots being radially offset from each of the second discharge slots, without any overlap between the first and second discharge slots.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

The invention relates to a turbomachine module (1), comprising: - a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), - a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).

Classes IPC  ?

• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques
• B64C 11/44 - Mécanismes de changement de pas des pales électriques
• F01D 7/00 - Rotors à aubes réglables en marche; Leur commande
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

A method for acquiring data for detecting damage to a bearing, comprising the following steps: (a) Obtaining (S10) a vibration signal from the bearing over a period of time; (b) determining (S14) spectrograms of said vibration signal at various instants of the period of time; (c) detecting (S22) the peaks on each spectrogram; (d) from among the detected peaks, retaining (S24) the peaks that, in spectrograms corresponding to successive instants and transformed through synchronous resampling at a rotational speed of the bearing, would be present at the same frequency, with a predetermined tolerance; (e) identifying (S26) spectral lines corresponding to the retained peaks; (f) storing (S44) information representative of said spectral lines in a record able to be used by a unit for detecting damage to the bearing.

Classes IPC  ?

• G01H 1/00 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur
• G01M 13/045 - Analyse acoustique ou des vibrations

Abrégé

The invention relates to a method for determining a predictive model of a pressure ratio P1/P2 for a predefined type of dual-flow turbine engine (100) comprising primary (VP) and secondary (VS) flows which are separated by a core compartment (110), the pressure P1 corresponding to an air pressure within the core compartment, the pressure P2 corresponding to an air pressure in the secondary flow. Moreover, the method comprises: - a step (E10) of acquiring, on a test turbomachine operating like the predefined type, at respective measurement times, sets of measurements each comprising a measurement P1, a measurement P2, a measurement M of a Mach number, and a measurement PCN12R representative of a low pressure speed, - a step (E20) of obtaining the sets of measurements by means of a processing device, - a step of supervised learning (E30), by the processing device and from the sets of obtained measurements, of a predictive model of the P1/P2 ratio according to the M number and the speed PCN12R which are considered to be explanatory variables.

Classes IPC  ?

• A61K 31/4427 - Pyridines non condensées; Leurs dérivés hydrogénés contenant d'autres systèmes hétérocycliques

Abrégé

The present invention relates to a bypass fan casing (4), characterised in that it comprises a single wall (14) configured to form at least part of an outer skin of a nacelle (17), said wall (14) comprising at least one reinforcement (13, 130) for stiffening the fan casing (4), at least one such reinforcement (13) being made up of a part of the wall (14) forming at least one annular zone (13A, 13B) projecting towards the inside of the nacelle and/or having an extra thickness, said reinforcement (13) being further configured for attaching the fan casing (4) to arms (7) that pass through a secondary flow stream of the turbojet engine.

Classes IPC  ?

• F01D 25/26 - Carcasses d'enveloppe doubles; Mesures contre les tensions thermiques dans les carcasses d'enveloppe

Abrégé

The invention concerns a turbine blade, comprising a root, a vane (12) comprising a leading edge and a trailing edge (17) and a pressure-side wall and a suction-side wall, and comprising cooling vents (26, 27) at the trailing edge (17), this vane also comprising: ? first (T1) and second (T2) serpentine circuits (T1); ? each serpentine circuit (T1, T2) comprising several ducts (CA1, CM1, CT1, CA2, CM2, CV2, CT2) extending in the span direction (EV), being connected to each other by angled portions; ? each serpentine circuit (Tl, T2) being supplied with air by its duct (CA1, CA2) that is closest to the leading edge (16); and in which the vents (26, 27) are supplied by the first and by the second serpentine circuit (Tl, T2).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

The invention concerns a method for regulating the acceleration of a turbomachine, the turbomachine comprising a combustion chamber, a high-pressure turbine situated downstream from the combustion chamber and that rotates a high-pressure shaft, and a low-pressure turbine situated downstream from the high-pressure turbine and that rotates a low-pressure shaft, characterised in that the method comprises the following steps: - Injecting (100) mechanical power onto the high-pressure shaft until the speed of the high-pressure shaft reaches a target value, then - Drawing (200) mechanical power from the high-pressure shaft in order to maintain the speed at the target value.

Classes IPC  ?

• F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/26 - Démarrage; Allumage
• F02C 7/266 - Allumage électrique

Abrégé

The invention relates to an assembly (10) for supporting and guiding a drive shaft (1) for an aircraft turbine engine, comprising a bearing support (3) having a cylindrical housing (30) for receiving an outer ring (21) of a bearing (2), and a device for rotationally retaining (5) a first portion (210) of the outer ring which is detached from its attachment to the bearing support; and when the above-mentioned detachment occurs: - the free outer peripheries (521) of the first teeth (52) of the first portion (210) are configured to cooperate by wedge effect in the tangential direction with complementary inner surfaces (532) of the housing (30) of the bearing support ( 3), - and/or the free inner peripheries (531) of the second teeth (53) inside the housing (30) are configured to cooperate by wedge effect in the tangential direction with complementary outer surfaces (522) of the outer ring (21).

Classes IPC  ?

• F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F04D 29/053 - Arbres
• F04D 29/057 - Paliers hydrodynamiques

Abrégé

A system REG for regulating a physical parameter (y) of a real turbomachine system F(p) from a physical setpoint parameter (yc), the regulation system REG comprising a system OPTK for optimising the parameterisation gain K during the regulation, the optimisation system OPTK comprising a stability correction module (2) determining a first gain component K1, a response time correction module (3) determining a second gain component K2, the stability correction module (2) being designed to inhibit the response time correction module (3) when an instability is detected during the regulation of the physical parameter (y), and a determination module (4) configured to determine the parameterisation gain K as a function of the previously determined first gain component K1 and second gain component K2.

Classes IPC  ?

• G05B 11/01 - Commandes automatiques électriques
• G05B 13/02 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques

Abrégé

Turbine for a turbomachine, comprising an annular row (20) of movable blades (20a) surrounded by a support ring (26) which is made of an abradable material (24) and borne by a casing (10), and a nozzle (30) which is mounted downstream of the annular row (20) of movable blades (20a) and comprises a means for hooking on a casing (10) support means, the hooking means comprising a radially outer spoiler (38) bearing radially inwardly on a cylindrical wall (12) of the support means, the support means further comprising an annular wall (14) which extends radially inwardly from the cylindrical wall (12) and the radially inner end of which is engaged in an annular groove (28) of the ring (26), and wherein a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12) of the support means.

Classes IPC  ?

• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations

Abrégé

The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (01) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.

Classes IPC  ?

• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F02C 9/16 - Commande du débit du fluide de travail
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

The invention concerns a turbomachine, the upstream part of the annular combustion chamber (110) of which is attached to the external casing (138), by means of pins, each having a ball-joint coupling. For each pin: - the ball-joint coupling (69) is established between the pin (160) and a part (86) of the external casing (138), and - the pin can also slide radially, or with a radial component, by means of a sliding action (72) established between the pin and a tubular part (70b) of the outer annular ferrule (114) and/or the bottom annular wall (154) of the chamber (118).

Classes IPC  ?

• F23R 3/60 - Structures de support; Moyens de fixation ou de montage
• F23R 3/50 - Chambres de combustion comprenant un tube à flamme annulaire à l'intérieur d'une enveloppe annulaire

Abrégé

The present intention relates to a method for resetting the static pressure model (mod_Ps3(PCN25R)), called "Ps3 model", upstream of a combustion chamber in a turbine engine comprising a compressor (3), the Ps3 model being used to arbitrate between two acquisition channels (V10, V20) of the static pressure (Ps3), called "Ps3 pressure", upstream of the combustion chamber, the two acquisition channels (V10, V20) using two sensors (10, 20), the model expressing the pressure Ps3 as a function at least of the speed (PCN25R), called "PCN25R speed", of the compressor (3), and comprising the following steps: E1: measuring a value of the pressure Ps3 using one of the two sensors (10, 20); E2: resetting the Ps3 model using the measurement of the value of Ps3.

Classes IPC  ?

• B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

Abrégé

Turbomachine (1) comprising a cone (40) positioned at an upstream end and secured to rotate as one with the low-pressure shaft (20), a system for deicing said cone (40) comprising resistive heating elements (52) positioned in the cone (40), an energy transfer system (54), a source of electrical power (56) coupled to the high-pressure shaft (20) and connected to the energy transfer system (54) by a set of switches (58), and a computer (60) configured to define a setpoint for the power for the deicing of the cone (40) as a function of ambient pressure and temperature data and of a regime of operation of the low-pressure shaft (20), and as a function of the electrical power supplied by the source of electrical power (56), and to define a duty cycle for the switching of the set of switches (58) in order to deliver electrical power to the resistive heating elements (52).

Classes IPC  ?

• B64C 11/14 - Cônes de pénétration
• F02C 7/047 - Chauffage pour prévenir le givrage

Abrégé

The invention relates to a mould (1) intended to be used for manufacturing a monocrystalline component by the pouring of metal and epitaxial growth, the mould comprising a cavity (10) in which the component is intended to be formed, and a housing (12) of elliptical cross section in which a monocrystalline seed (2) is placed, the seed having an elliptical cross section defined by a minor axis and a major axis, the housing being in fluidic communication with the cavity via an opening (13) of circular cross section via which molten metal is intended to flow, the monocrystalline seed and the opening being centred on the one same vertical axis (Z), wherein the minor axis and the major axis of the cross section of the seed are oriented according to the secondary crystallographic orientations of the monocrystal that forms the monocrystalline seed. The invention also relates to the corresponding manufacturing method.

Classes IPC  ?

• B22C 9/04 - Emploi des modèles perdus
• B22D 27/04 - Action sur la température du métal, p.ex. par chauffage ou refroidissement du moule
• C30B 11/14 - Croissance des monocristaux par simple solidification ou dans un gradient de température, p.ex. méthode de Bridgman-Stockbarger caractérisée par le germe, p.ex. par son orientation cristallographique

Abrégé

The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closing the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined from the static angle, corresponding to the fact that the joint (J1) remains compressed and seals the closing of the orifice (O1), the dead zone is recorded and the signal (SC1) for controlling the actuator (V1) is generated by the computer as a function of the dead zone.

Classes IPC  ?

• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz

Abrégé

The invention relates to a method for monitoring an engine control unit having at least two separate paths, each of the paths comprising at least: - means for carrying out a given application task AS, the application task AS consisting in part of a plurality of calculations which are performed consecutively and between which there are periods of latency; - a first component capable of performing the calculations; and - a second component capable of storing data. The application tasks AS of the paths are capable of communicating, and the method comprises the following steps: a) detecting a period of latency; b) performing, during said period of latency, a test of the operational state of at least one of the components; and c) determining a state of the component corresponding to a failure state or a healthy state.

Classes IPC  ?

• G06F 11/16 - Détection ou correction d'erreur dans une donnée par redondance dans le matériel
• G06F 11/22 - Détection ou localisation du matériel d'ordinateur défectueux en effectuant des tests pendant les opérations d'attente ou pendant les temps morts, p.ex. essais de mise en route

Abrégé

Disclosed is a cascade-type thrust reversal device for a turbomachine (1) of an aircraft, comprising a cascade (80) having first partitions (82), second partitions (83) intersecting the first partitions (82), and cavities (84), and a casing (71) having a housing (75) into which the cascade (80) can be inserted in a first direction (DA), the casing (71) and the cascade (80) being able to move in translation relative to one another in the first direction (DA). The casing (71) comprises a perforated wall (72) that is intended to be in contact with an air flow (F) and has orifices (722), and wall strips (724) that do not have orifices and are intended to face the first walls (82) of the cascade (80) when the device (70) is in a first position in which the cascade (80) is disposed entirely in the housing (75).

Classes IPC  ?

• F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
• F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
• G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p.ex. sandwiches
• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance

Abrégé

A cascade-type thrust reversal device (70) for a turbomachine (1) of an aircraft, comprising a thrust reversal cascade (80) and a casing (71), the cascade (80) having first cavities (84) and the casing (71) comprising an opening (76) defining a housing (75) into which said cascade (80) can be inserted in a first direction (DA), and the casing (71) and said cascade (80) being able to move in translation relative to one another in the first direction (DA) between a first position of the device (70), in which position the cascade (80) is disposed entirely in the housing (75), and a second position of the device (70), in which position said cascade (80) is at least partially outside said housing (75). The casing (71) comprises an acoustic treatment panel (74) having second cavities (744) extending in a second plane parallel to the first plane, each first cavity (84) facing a second cavity (744) when the device (70) is in the first position so as to form an acoustic treatment cell (710).

Classes IPC  ?

• F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
• F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
• G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p.ex. sandwiches
• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance

Abrégé

A cascade (80) for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade (80) comprising first partitions (82) extending in a first direction (D_A), second partitions (83) extending in a second direction (D_C) orthogonal to the first direction (D_C), the second partitions (83) extending in a third direction (DR) secant to a plane comprising first and second directions (D_A and D_C) between first and second ends (85 and 86). Each second partition (83) forms, with reference planes (Pr) parallel to the second direction (D_C) and to the third direction (DR), a plurality of different angles (?1 to ?4) at separate positions (H1 to H4) of the height (H) of the second partitions (83) separating the first end (85) from the second end (86) of the second partitions (83), each angle (?1 to ?4) being formed between a reference plane (Pr) and the tangent to the second partition (83) taken at the intersection between said corresponding reference plane (Pr) and the second partition (83) at the corresponding position (H1 to H4) of the height (H) of the second partition (83).

Classes IPC  ?

• F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
• F02K 1/82 - Parois des tubulures de jet, p.ex. chemises

Abrégé

The invention relates to a turbine engine separate flow mixer (2) centred on a longitudinal axis (X-X), comprising an exhaust housing (6), a shroud (4) directly connected to the exhaust housing (6) and intended to mix the flows originating from the turbine engine, said shroud (4) comprising a metal sheet formed by a series of first and second longitudinal strips (4a, 4b) circumferentially distributed around the longitudinal axis of the mixer by circumferentially placing the second strips (4b) on either side of the first strips (4a), the first and second strips being configured to form the shroud (4) at rest and by making grooves in the shroud, the grooves being defined by an alternation of internal lobes and of external lobes.

Classes IPC  ?

• F02K 1/38 - Introduction d'air à l'intérieur du jet
• F02K 1/48 - Tuyères ondulées

Abrégé

A cascade (80) for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade (80) comprising first partitions (82) extending in a first direction (DA), second fixed partitions (83) extending in a second direction (DC) orthogonal to the first direction (DA), and a frame (81) within which the first and second partitions (82, 83) extend, the frame (81) comprising at least two fixed walls (810, 815) extending in the first direction (DA), and at least part of each first partition (82) extending between two second partitions (83). At least one first partition (82) is movable in the second direction (DC) between a first position in which said first partition (82) is distant, in the second direction (DC), from said fixed walls (810, 815) so as to form a plurality of resonant cavities (84) with the first partitions (83) and/or the fixed walls (810, 815), and a second position in which said one first partition (82) is in contact with a fixed wall (810, 815) or another first partition (82).

Classes IPC  ?

• F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante

Abrégé

The invention relates to a turbine vane comprising a root carrying a blade terminated by a tip in the form of a squealer tip, the blade having an intrados wall and an extrados wall, as well as a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall, said blade also comprising: - a serpentine median circuit (28), including a first radial pipe (41) that collects air at the root and is connected by a first bend (46) to a second radial pipe (42) that is connected by a second bend (47) to a third radial pipe (43); - a cavity (36) under the squealer tip running along the extrados wall (21) and extending from a central region of the tip (S) to the trailing edge (17); - a central radial pipe (34) collecting air at the root and extending between at least two of the three pipes (41, 42, 43) of the median circuit (28) and directly supplying the cavity (36) under the squealer tip.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• B22C 9/10 - Noyaux; Fabrication ou mise en place des noyaux
• B22C 9/24 - Moules pour pièces de forme particulière pour pièces évidées

Abrégé

Counter-rotating turbine (C) for a turbomachine (10) extending around an axis of rotation (X) and comprising: an internal rotor (22) turning about the axis of rotation (X) and comprising at least one internal mobile blade (220) rotatably supported by a first shaft (26); an external rotor (20) turning around the axis of rotation (X) in a direction opposite that of the internal rotor (22) and comprising at least one external mobile blade (200) rotatably supported by a second shaft (24) that is coaxial to the first shaft (26), the first and second shafts (24, 25) extending axially from upstream to downstream of the turbine (C), wherein the first shaft (26) is guided in rotation by a first bearing (62) arranged between the first shaft and an upstream casing (60) of the turbine, and the second shaft (24) is guided in rotation by a second bearing (72) arranged between the second shaft (24) and the upstream casing (60) of the turbine.

Classes IPC  ?

• F02C 3/067 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux comportant des rotors contra-rotatifs

Abrégé

The invention relates to a method for repairing a vane (1) made of composite material, which extends along a so-called axial direction (X), said vane (1) comprising a root (2) and a blade (3), wherein the axial end thereof, opposite the root (2), has an area to be repaired, said blade (3) comprising an intrados surface (4) and an extrados surface (5).

Classes IPC  ?

• B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
• B29C 73/24 - Appareils ou accessoires non prévus ailleurs
• F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support

Abrégé

An aircraft turbojet engine (1) comprising a fan (11) configured to provide a reverse thrust and a nacelle comprising an air intake (2), the air intake (2) comprising at least one circulation duct (3) in the annular cavity (20) opening, on the one hand, at the air intake lip (23) and, on the other hand, at the inner wall (21) and/or the outer wall (22) so as to promote a reverse thrust phase, the air intake (2) comprising at least one cover member (31, 32) mounted to move between a covered position, in which the cover member (31, 32) closes the circulation duct (3) at the air intake lip (23) and an uncovered position, in which the cover member (31, 32) opens the circulation duct (3) at the air intake lip (23).

Classes IPC  ?

• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• F02C 7/042 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction à géométrie variable
• F02K 1/64 - Inversion du flux de la soufflante

Abrégé

Disclosed is a method for using an aircraft turbojet engine (1) comprising an air inlet (2) comprising a plurality of rectifier vanes (3), each rectifier vane (3) being mounted such that it can move between a retracted position to assist the thrust phase and a deployed position (B) in which the rectifier vane (3) protrudes from the inner wall (21) in a radially inward direction in order to rectify the reverse air flow (F-INV) of the inner wall (21) to assist a thrust-reverse phase, in which method at least one rectifier vane (3) is in the retracted position during a turbojet engine thrust phase (1), the method comprising, during a thrust-reverse phase of the turbojet engine (1), a step of moving the rectifier vane (3) to the deployed position.

Classes IPC  ?

• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• F02C 7/042 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction à géométrie variable
• F02K 1/66 - Inversion du flux de la soufflante en inversant les aubes du ventilateur

Abrégé

Disclosed is a method for treating an internal defect (10) in a part (1) made of a material, said method involving: a) detecting and locating the internal defect (10) in the part; b) defining, inside the part, at least one target volume (4) which at least partially includes the defect; c) for each target volume (4), simultaneously irradiating the target volume by at least two beams (2) which converge in the target volume and are continuous, whereby a treated area is obtained. The energy applied to the target volume by each beam is less than a threshold energy for sintering the material, and the sum of the energies applied to the target volume by each of the beams is greater than or equal to a transformation threshold energy that corresponds to the threshold energy for sintering or melting the material; the material of the part is partially transparent to said beams.

Classes IPC  ?

• B29C 73/34 - Appareils ou accessoires non prévus ailleurs pour presser localement ou pour chauffer localement pour chauffer localement
• B23K 26/53 - Travail par transmission du faisceau laser à travers ou dans la pièce à travailler pour modifier ou reformer le matériau dans la pièce à travailler, p.ex. pour faire des fissures d'amorce de rupture
• B23P 6/04 - Réparation de pièces ou de produits métalliques brisés ou fissurés, p.ex. de pièces de fonderie
• B29C 35/08 - Chauffage ou durcissement, p.ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire

Abrégé

The present invention relates to a bypass air/fluid heat exchanger (2) for a turbofan engine. According to the invention, this exchanger (2) comprises: - an annular outer shroud (3) with two walls, an inner wall (32) and an outer wall (31), - an annular inner shroud (4) concentric with the outer shroud (3), - a series of OGV guide vanes (5) which connect said outer shroud to said inner shroud, - and a circulation circuit (6) for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit (6) is formed in the body of the outer shroud (3) and in the body of at least one of the OGV guide vanes (5), this circulation circuit (6) opening at the two respective ends thereof into an inlet opening (34) and into an outlet opening (35), formed through said outer wall (31) of the outer shroud, and the two shrouds (3, 4), the OGV guide vanes (5) and the circulation circuit (6) of said fluid are integral.

Classes IPC  ?

• F28D 7/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/26 - Carcasses d'enveloppe doubles; Mesures contre les tensions thermiques dans les carcasses d'enveloppe
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F28F 1/26 - Eléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p.ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire et s'étendant transversalement les moyens faisant partie intégrante de l'élément

Abrégé

A process for using an air input (2) of a turboreactor nacelle (1) of an aircraft, comprising an air input lip (23) which comprises at least one fixed portion and at least one portion (3, 3', 4, 4', 5, 5', 6, 6', 7) which can be moved between a first position, in which the air input lip (23) has an aerodynamic profile so as to guide the internal air flow over the internal wall (21) in order to promote a thrust phase, and a second position (B), in which the portion (3, 3', 4, 4', 5, 5', 6, 6', 7) is displaced in relation to the fixed portion so that the air input lip (23) has a second radial thickness (EB) in the second position (B) which is less than the first radial thickness (EA) in the first position so as to promote a reverse thrust phase.

Classes IPC  ?

• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• F02C 7/042 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction à géométrie variable
• F02K 1/66 - Inversion du flux de la soufflante en inversant les aubes du ventilateur

Abrégé

L'invention concerne un ensemble (10) pour turbomachine comprenant une conduite (12) reliée à une extrémité (12a) à des moyens (14) d'alimentation en air pressurisé et à une extrémité (12b) opposée à un équipement (16) de la turbomachine, la conduite (12) comportant une portion coudée (12c) destinée à former en utilisation un point bas de la conduite (12), ladite portion coudée (12c) comportant un trou (18) de purge premier d'eau de la conduite (12), dans lequel il comprend en outre un orifice (20) agencé en aval du trou (18) de purge.

Classes IPC  ?

• F01D 25/32 - Recueil de l'eau de condensation; Drainage
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue

Abrégé

The invention relates to a contra-rotating turbine (C) of a turbine engine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum to which an inner moving blading (22) is attached, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) to which an outer moving blading (20) is attached, the outer moving blading (20) comprising at least one attachment rod (212) extending through an opening (51) of the outer drum (50), the outer moving blading (20) being attached to the outer drum (50) via a clamping means (100) attached to the attachment rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the attachment rod (212) in the opening (51) of the outer drum (50).

Classes IPC  ?

• F01D 1/26 - "Machines" ou machines motrices à déplacement non positif, p.ex. turbines à vapeur caractérisées par des rotors contra-rotatifs soumis au même courant de fluide énergétique sans aubes ou structures analogues intermédiaires sur les stators traversées par le fluide de travail principalement dans le sens axial
• F01D 5/03 - Organes annulaires de support des aubes avec des aubes placées sur la périphérie interne de l'anneau et s'étendant radialement vers l'intérieur, c.à d. rotors inversés
• F01D 5/26 - Dispositifs antivibratoires non limités à la forme ou à la structure des pales ou aux connections aube à aube
• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales
• F02C 3/067 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux comportant des rotors contra-rotatifs

Abrégé

The present invention concerns a method for monitoring an actuating system of a movable component, in particular a movable component of a turbomachine such as a nozzle or a blade, the actuating system comprising a control device configured to deliver a position instruction to a first cylinder and a second cylinder, each cylinder being configured to deliver a position feedback measurement in response to the position instruction, the method being implemented in a monitoring system and comprising, - a first monitoring mode in which the deviations between the position feedback measurements of the two cylinders are detected; - a second monitoring mode in which the deviations between the position feedback measurements of the two cylinders are not detected; method in which the second mode is selected when at least one of the two position feedback measurements is in a transient phase.

Classes IPC  ?

• F01D 17/10 - Organes de commande terminaux
• F02K 1/15 - Commande ou régulation
• F02K 1/76 - Commande ou régulation des inverseurs de poussée

Abrégé

Aircraft turbomachine blade (102), said blade comprising at least one inner cavity (100) for circulating a ventilation air flow, said cavity comprising a wall (104) which comprises first projecting elements (106) oriented in a first direction and forming air flow disrupters, said wall further comprising at least a second projecting element (108) oriented in a second direction different from the first direction, said second element and at least one of the first elements overlapping each other in one area, the blade being characterised in that the or each first element which overlaps the second element has a height (H2, H4') which is greater than that (H1) of the second element in the area and greater than that (H3) of the other first elements of the wall, in order to retain its disruptive function along the entire length thereof.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third turbomachine control quantity, each of which can become saturated as a function of the turbomachine operating parameters. The method comprises a first multi-variable correction (120) delivering a first value for the three control quantities, a selection (130) of the first control quantity to be delivered as a function of a minimum value, of a maximum value and of the value determined by the first correction, a second multi-variable correction (140) delivering a second value for the second and third control quantities, and a selection (150) of the values of the second and third control quantities to be delivered according to the values determined during the first correction and those determined during the second correction.

Classes IPC  ?

• F02C 9/48 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel
• B64C 11/48 - Ensembles de plusieurs hélices coaxiales
• F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion

Abrégé

The invention relates to a tool for preforming a fibrous preform, comprising: - an inflatable first membrane (11) intended to accept the fibrous preform, - a second membrane (18) intended to attach to the first membrane (11) via a fixing system (20) in such a way as to form a fluidtight internal cavity (19) between the first and second membranes, and - an evacuation device (25) for creating a vacuum in the internal cavity between the first membrane (11) and the second membrane (18).

Classes IPC  ?

• B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
• B29C 70/34 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
• B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant une pression isostatique, p.ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible

Abrégé

A weaving installation (400) comprises a loom (100 intended to produce a woven texture by weaving together a plurality of threads, at least some of the threads of the plurality of threads being carbon threads (210, 211, 212, 213, 214, 215), the carbon threads each being stored individually on one package of a plurality of carbon thread storage packages (220, 221, 222, 223, 224, 225) present upstream of the loom. The installation also comprises a plurality of pairs of first and second electrical contacts (301, 302; 303, 304; 305, 306; 307, 308; 309, 310; 311, 312) present between the storage packages (220, 221, 222, 223, 224, 225) and the loom (100). Each pair of first and second electrical contacts is present on the path of a carbon thread, the first and second contacts of each pair being intended to be in electrical contact with a given carbon thread. The contacts of each pair of first and second contacts are also connected to an open-circuit detection circuit (230).

Classes IPC  ?

• D03D 51/28 - Casse-chaîne électriques

Abrégé

The invention relates to a silicon heating mat (10), said mat (10) being formable and deformable and comprising a matrix (14) made of elastic material, in which at least one cavity (16) is arranged that fully passes through the matrix (14), said at least one cavity (16) being intended to accommodate a resistive filament (18) connected to a heating cycles management unit (12). Furthermore, said at least one cavity (16) has an undulating layout, with each resistive filament (18) being able to move inside said at least one cavity (16), and each resistive filament (18) having a zigzag or spiral shape.

Classes IPC  ?

• H05B 3/34 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes flexibles, p.ex. grillages ou tissus chauffants

Abrégé

The invention relates to a turbine engine vane (20) comprising a blade (21) extending along a radial axis and a first cooling circuit (28) arranged inside the blade, the first cooling circuit (28) comprising a first cavity (34) and a second cavity (35) disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition (36) having a radially internal free end (37), which at least partly demarcates a first coolant passage (40) connecting the first and second cavities. According to the invention, the radially internal free end (37) is enlarged by having a general transverse section substantially in the form of a keyhole.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

The invention relates to a turbine engine blade (20) comprising: - an airfoil (21) with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge (26) and downstream by a trailing edge (27), - a cooling circuit (28) which comprises an internal cavity extending inside the airfoil and a plurality of outlet openings each oriented substantially along a longitudinal axis X, each outlet opening communicating with the cavity and being arranged in the vicinity of the trailing edge, and - a calibration device (33) arranged in the cavity and provided with calibration conduits (34) which are arranged substantially opposite the outlet openings. According to the invention, the calibration conduits (34) each comprise an oblong transverse section which is substantially perpendicular to the longitudinal axis.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

Disclosed is a method for controlling the braking of the wheels of an aircraft, in which method the braking of the wheels of the aircraft is controlled by a wheel braking controller (14) actuating wheel brakes (10) of the aircraft as a function of both a deceleration control request (16) and a request for deployment of the thrust reversers (24).

Classes IPC  ?

• B64C 25/42 - Aménagement ou adaptation des freins
• B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p.ex. bogies à roues multiples

Abrégé

The invention relates to a tubular ventilation sleeve (1) for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and comprising a perforated tubular wall (1a) around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall (1b), characterized in that it further comprises support beams (7) when the sleeve (1) is made by additive manufacturing, said beams (7) extending inside the sleeve (1) between the tubular wall (1a) and the bottom wall (1b) and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall (1a) and the bottom wall (1b) and the last side of which is free and extends inside the sleeve, perforations (2) in the tubular wall (1a) being provided between the support beams (7).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

The invention relates to a method for regulating a temperature of the exhaust gases of a turbomachine (1), the method comprising the following steps: - regulating the injection of fuel into a combustion chamber (5) of the turbomachine (1) such that the turbomachine (1) generates a target thrust; - regulating the injection of mechanical power by an electric motor (10) to a shaft (8, 9) driven to rotate by a turbine (6, 7), the electric motor (10) being activated when a clearance between a casing (62) and blades (61) of the turbine (6, 7) exceeds a threshold value.

Classes IPC  ?

• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
• F02C 9/48 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel

Abrégé

The invention relates to an assembly for a turbomachine extending along an axis (X) and comprising: - a ferrule (32) designed to define a fan duct (5) of a gas stream of the turbomachine, - a fan casing (2) radially surrounding the ferrule (32) and defining with the ferrule (32) the fan duct (5), - a rectifier (6) comprising a plurality of vanes (7) comprising a first vane (7a) and a second vane (7b) adjacent to the first vane (7a), the vanes defining between them a converging flow channel (13) designed to direct and accelerate the stream by means of an inlet section (14a) included in a plane non-perpendicular to the axis of the turbomachine and an outlet section included in a plane (14b) perpendicular to the axis (X) of the turbomachine, the first vane (7a) and the second vane (7b) each having an unducted downstream portion which forms a trailing edge.

Classes IPC  ?

• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant

Abrégé

The invention relates to a method for detecting a possible fuel leak in an oil circuit of an aircraft engine, said aircraft having at least one pair of identical engines equipped with respective oil circuits, said pair of engines being associated with at least one quadruplet of measurements acquired beforehand at a measuring time during operation of the engines of the pair, said measurements corresponding to a pressure measurement and a temperature measurement of the fluid contained in each of the oil circuits of the engines of the pair. Moreover, the method includes: - a step (100) of determining a quantity Q representative of a possible difference in operation between the engines of the pair, depending on the quadruplet of measurements, - a step (200) of comparing the quantity Q with a threshold value determined beforehand, so as to obtain a comparison result, - a step (300) of detecting a possible leak of fuel in the oil circuit of one of the engines of the pair, depending on the comparison result.

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F01D 25/18 - Systèmes de lubrification

Abrégé

The invention concerns a bypass turbomachine (1) with a primary flow path and a secondary flow path, comprising: - a low-pressure body comprising a low-pressure compressor (120) connected to a low-pressure turbine (122) via a low-pressure shaft (124), - a high-pressure body comprising a high-pressure compressor (130) connected to a high pressure turbine (132), via a high-pressure shaft (134), - a low-pressure power take-off system (220) comprising an electrical generator (226), configured to take power (W12) from the low-pressure body, wherein - the turbomachine comprises a debris removal system (500), located between the two compressors (226, 236), - the low-pressure power take-off system (220) is configured to take power (W12) from the low-pressure shaft (124) using the resistive torque of the electrical generator (226), in order to avoid a risk of surging.

Classes IPC  ?

• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

The invention relates to a drive shaft (50) of an aircraft turbine engine, comprising: - a first portion (52) and a second portion (54), - connecting means (56) connecting said first and second portions and being configured to transmit a torque from said second portion to said first portion, said connecting means comprising at least one bellows (70) comprising: - a first section (72) having a diameter greater than the diameters of said first and second portions, - second sections (74) flanking said first section, said drive shaft being characterised in that said first section includes at least one fusible section (76) comprising at least one through-hole (78) and being configured to break when the value of a torque applied to said first portion exceeds a predetermined threshold value.

Classes IPC  ?

• F16D 9/08 - Accouplements avec organe de sécurité pour le désaccouplement par rupture due au cisaillement sur une zone unique entourant l'axe de rotation, p.ex. gorges de cisaillement sur les arbres
• F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16C 3/00 - Arbres; Manivelles; Vilebrequins; Excentriques
• F16D 3/12 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement adaptés à des fonctions particulières spécialement adaptés à un emmagasinage de l'énergie pour absorber les chocs ou vibrations

Abrégé

Method for repairing a blade (10) of a turbomachine rotor, particularly a turbomachine fan, this blade comprising a vane (12) made from an organic-matrix composite and a metallic shield (14) bonded to a leading edge of the vane, the metallic shield (14) having a damaged region (20), the method comprising a step of resetting the leading edge of the vane, a step of cooling the entire vane, followed by a step of refilling the damaged region (20) by adding a metallic material to this damaged region (20) and melting the material using a laser, and a step of tailoring the damaged region (20) by machining the molten material.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
• F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion

Abrégé

Disclosed is a method for repairing a composite material part (10), comprising: - producing a hollowed-out portion (30) by removing the composite material in a damaged area (20), - producing grooves (110, 120) extending on the two faces (11, 12) of the part (10) from the edges (32, 34) of the hollowed-out portion, - producing a plurality of orifices (130) in the thickness of the part, opening into the grooves, - three-dimensional weaving of a fibrous preform of a filling part (40, 50) comprising a central portion (41, 51) having a shape corresponding to the shape of the hollowed-out portion and a plurality of fibre bundles (420, 450) extending from the central portion (41, 51), - placing the filling preforms (40, 50) respectively on one or other face of the part (10) with the fibre bundles present in the grooves present on the faces of the part and in the orifices of the plurality of orifices (130) so that the fibre bundles open into the grooves present on the opposite face of the part, - impregnating the fibrous filling preforms (40, 50) with a resin precursor of a matrix, - transforming the resin into a matrix in order to obtain a filling part made of composite material (60) comprising a fibrous reinforcement densified by a matrix.

Classes IPC  ?

• B29C 73/14 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des éléments en deux parties qui sont réunies après avoir été posées chacune sur un côté de l'objet
• B64F 5/40 - Entretien ou réparation d’aéronefs
• B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
• B29C 70/24 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• B29C 73/26 - Appareils ou accessoires non prévus ailleurs pour le prétraitement mécanique

Abrégé

Method for controlling a fuel-metering device with a mobile metering element, comprising at least two iterations of the following steps: - detecting (E1) a potential change in operational status of one of two metering-element position sensors, if no change in operational status is detected, determining (E2_1) the position of the metering element from a mean of the measurements from the sensors, or else determining (E2_2) said position from the sensor that is not defective, - determining (E4) a fuel flowrate setpoint, converting (E5) the fuel flowrate setpoint, - determining (E6) a metering-element movement command, commanding (E7) the position of the metering element and, if a change in operational status is detected, calculating an instantaneous fuel flowrate from the position of the metering element and, during the second iteration of the method, determining the flowrate setpoint as a function of the instantaneous flowrate in order to make the position setpoint correspond to the position of the metering element.

Classes IPC  ?

• F02C 9/32 - Commande de l'alimentation en combustible caractérisée par l'étranglement de l'admission du combustible
• F02C 9/26 - Commande de l'alimentation en combustible

Abrégé

The invention relates to a combustion chamber comprising an end wall (4) comprising at least one opening (5), at least one sleeve (12) mounted upstream of the end wall (4) and fastened to the end wall (4), a closure ring (13) delimiting an annular groove (11) with the sleeve (12) and fastened to the sleeve (12), at least one air- and fuel-injection system (6), having an axis (A), mounted in the opening (5) of the end wall (4), the injection system (6) comprising an annular rim (10) extending radially with respect to said axis (A) and being mounted in said groove (11) with a radial clearance, and a deflector (14) situated downstream of the end wall (4) and fastened to the sleeve (12) and/or to the end wall (4).

Classes IPC  ?

• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F16B 5/10 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par assemblages à baïonnette
• F23R 3/50 - Chambres de combustion comprenant un tube à flamme annulaire à l'intérieur d'une enveloppe annulaire
• F23R 3/60 - Structures de support; Moyens de fixation ou de montage

Abrégé

The invention relates to a blade pivot (2) of adjustable orientation for a turbomachine fan hub, comprising a block (4) having retaining means (10) configured to retain a fan blade root (12) and coupling means (16) for the transmission of a torque, a ball-type rolling bearing (26) for taking up centrifugal forces having an inner ring (28), a clamping nut (42) screwed onto an external thread (44) of the block in order to clamp the inner ring of the ball-type rolling bearing for taking up centrifugal forces onto the block, a rolling bearing (34) for taking up transverse forces, a wedging transmission ring (18) positioned inside the inner radial end of the block and provided with coupling means (20) cooperating with the coupling means (16) of the block, and means (22, 24) for locking the wedging transmission ring on the block.

Classes IPC  ?

• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
• F01D 7/02 - Rotors à aubes réglables en marche; Leur commande ayant un réglage sensible à la vitesse
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

The invention relates to a turbomachine blade (54) comprising a body (60) that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall (66), an upper surface wall (68), a leading edge (70) located at a first longitudinal end of the body (60) and a trailing edge (72) located at a second longitudinal end of the body (60), characterized in that the body (60) of the blade (54) comprises a plurality of first pipes (74) that extend mainly along the direction of the main axis B, for circulation of a gas flow, and a plurality of second pipes (76) that extend mainly along the longitudinal direction, for circulation of a second gas flow.

Classes IPC  ?

• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F01D 5/14 - Forme ou structure
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/12 - Refroidissement
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
• F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur

Abrégé

A method for electrical discharge drilling of a hole (18) in a part (16) made of electroconductive material, in particular for an aircraft turbomachine, the method using an electrical discharge machine comprising a head (12) that can move relative to the part and has a consumable EDM electrode (10), which is of elongated shape and is translationally moved along its elongation axis, the method comprising the following steps: a) advancing the EDM electrode towards the part in order to drill a hole in the part; and b) retracting the EDM electrode and removing the EDM electrode from the hole, characterised in that it further comprises the following steps: c) laterally moving the head; d) advancing the EDM electrode towards the part in order to scan for the part; e) computing the effective depth of the hole drilled in step a).

Classes IPC  ?

• B23H 9/10 - Usinage d'aubes de turbine ou de buses
• B23H 9/14 - Réalisation de trous
• B23H 1/00 - Usinage par décharge électrique, c. à d. enlèvement de métal au moyen de séries de décharges électriques à cadence élevée entre une électrode et une pièce en présence d'un fluide diélectrique

Abrégé

The invention relates to a reducing assembly (26) comprising a planet carrier (27) that is flexible and fixed, borne by a casing (32) which surrounds it by means of two distinct connections with this casing (32), with means (44) for applying a torsional prestress to the planet carrier (27) between these two connections. Prestressing the flexible planet carrier (27) makes it possible to limit its level of mechanical stress when it is in service, in order to simplify its design and dimensioning.

Classes IPC  ?

• F16H 57/08 - TRANSMISSIONS - Parties constitutives générales des transmissions des transmissions à organes à mouvement orbital

Abrégé

The invention relates to a method for separating a first mechanical part (12) from a second mechanical part (14), wherein the second mechanical part (14) is bonded to the first mechanical part (12) by an adhesive film (16) along a connecting area, the first mechanical part (12) having a first specific thermal conductivity and the second mechanical part (14) having a second thermal conductivity that is higher than the first thermal conductivity, characterised in that it comprises at least one cooling step during which the second mechanical part (14) is cooled to a negative temperature and at least one stressing step during which the second mechanical part (14) is subjected to mechanical stress in order to cause the adhesive film (16) to break.

Classes IPC  ?

• B23P 15/04 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe d'aubes de turbine ou d'organes équivalents, en plusieurs pièces
• B26F 3/06 - Séparation par la chaleur
• B32B 43/00 - Opérations spécialement adaptées aux produits stratifiés et non prévues ailleurs, p.ex. réparation; Appareils pour ces opérations
• C09J 5/06 - Procédés de collage en général; Procédés de collage non prévus ailleurs, p.ex. relatifs aux amorces comprenant un chauffage de l'adhésif appliqué

Abrégé

The invention relates to a method for monitoring the state of health of at least two vibration sensors of a twin-spool turbomachine comprising a low-pressure spool and a high-pressure spool, one vibration sensor being located at the front of the turbomachine, and another vibration sensor being located at the rear of the turbomachine, each of the sensors being configured to measure the vibrations of the low-pressure spool and high-pressure spool at the front and at the rear of the turbomachine, the method being carried out in a processing unit (20) of the turbomachine, which processing unit is in communication with each of the sensors, the method comprising the following steps: - receiving the low-pressure speed (NBP) and high-pressure speed (NHP) of the turbomachine and, when the speeds are simultaneously in predetermined ranges, - receiving the front and rear vibration levels of the low-pressure and high-pressure spools which are recorded by each sensor; - establishing the mean of the values of the vibration levels of the low-pressure and high-pressure spools received over a predetermined receiving time; - establishing the state of health of the at least first and second vibration sensors from a comparison between the established mean values of the vibration levels of the low-pressure and high-pressure spools and predetermined thresholds.

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F01D 17/02 - Aménagement des éléments sensibles
• F01D 25/04 - Systèmes antivibratoires
• G01H 1/00 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur
• G01H 3/00 - Mesure des vibrations en utilisant un détecteur dans un fluide

Abrégé

The invention relates to an aerodynamic arm (100) for an aircraft turbine engine casing, characterised in that it comprises: - a tubular outer shell (110) having a generally elongate shape extending substantially along an axis (A-A), the shell (110) comprising axial ends (112) for connecting to a turbine engine casing; - an electrically conductive core (120) extending inside the shell (110) and having ends for electrically connecting to each of the ends (112) of the shell (110); and - an insulating material (130) configured to occupy a space provided between the core (120) and the shell (110).

Classes IPC  ?

• F04D 29/54 - Moyens de guidage du fluide, p.ex. diffuseurs
• F01D 5/14 - Forme ou structure
• F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F02C 7/20 - Montage ou bâti de l'ensemble fonctionnel; Disposition permettant la dilatation calorifique ou le déplacement
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
• F04D 29/02 - Emploi de matériaux spécifiés

Abrégé

An injector nozzle (43) for a turbomachine comprises a primary fuel circuit ending in a fuel ejection pipe (66), and a secondary fuel circuit comprising an annular end portion for ejecting fuel (68) arranged around the fuel ejection pipe. A portion upstream from the primary fuel circuit comprises an annular channel (70), which extends around the secondary fuel circuit and is defined by an external wall (72) of the injector nozzle. The injector nozzle comprises air intake channels (126) extending through the annular channel (70) and having inlets opening into the external wall (72) and outlets (130) opening into an annular air injection channel (124) arranged radially in the interior in relation to the end portion for ejecting fuel, around the fuel ejection pipe, and cooperating with the end portion for ejecting fuel in order to form an aerodynamic secondary injector.

Classes IPC  ?

• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23R 3/34 - Alimentation de différentes zones de combustion

Abrégé

The invention relates to a system and method for controlling an aircraft turbine engine. According to the invention, the control system (100) comprises: - a nominal-mode processing chain (110) comprising a global corrector (21) designed to control a speed of rotation of the turbine engine by delivering a position setpoint (C_WF) for a fuel metering device (11, 12), and a local corrector (23) designed to control a position of the fuel metering device by delivering a nominal-mode control current (I_nom), - a degraded-mode processing chain (120) comprising a direct corrector (122) designed to control the speed of rotation of the turbine engine by delivering a degraded-mode control current (I_dég), and - a mode management module (130) designed to deliver, to the fuel metering device, the nominal-mode control current (I_nom) in the absence of failure of a position sensor measuring a position of the fuel metering device, and the degraded-mode control current (I_dég) in the case of failure of the position sensor.

Classes IPC  ?

• F02C 9/32 - Commande de l'alimentation en combustible caractérisée par l'étranglement de l'admission du combustible
• F02C 9/46 - Commande de secours de l'alimentation en combustible

Abrégé

Tooling (3) for placing a propulsive assembly (2) from a horizontal position to a vertical position, comprising: - a front tool (4) comprising: a first assembly comprising a frame (19) configured to be positioned and maintained with respect to a front casing (14), said frame (19) comprising a first connection interface (20) configured to be connected to a first lifting system (8) such that said frame (19) is movable about an axis of rotation (R); a second assembly comprising a shaft configured to be positioned and maintained with respect to a rotor; a member for connection between said first assembly and said second assembly; - a rear tool (6) configured to be positioned and maintained with respect to said rear casing (7), said rear tool (6) comprising a second connection interface (23) configured to be connected to a second lifting system (10).

Classes IPC  ?

• B64F 5/50 - Manipulation ou transport des composants d'aéronefs
• F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
• F02C 7/20 - Montage ou bâti de l'ensemble fonctionnel; Disposition permettant la dilatation calorifique ou le déplacement

Abrégé

The invention relates to a propulsion system (100) for an aircraft, comprising at least one rotor (110) and a nacelle cowling (120) extending around the at least one rotor (110), said nacelle cowling (120) being sectored and comprising at least one sector (130a, 130b) which is fixed and sectors (141a, 141b, 142a, 142b) which are retractable in the peripheral direction (F1, F2) relative to an axis of rotation (X) of the rotor (110), characterised in that the retractable sectors (141a, 141b, 142a, 142b) comprise at least a first series of sectors (141a, 142a) which are telescopically retractable in or on at least one fixed sector (130a) and at least a second series of sectors (141b, 142b) which are telescopically retractable in or on at least one fixed sector (130b), the at least one fixed sector (130a, 130b) having an angular extent around the axis (X) which is less than or equal to 90°.

Classes IPC  ?

• B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
• B64D 29/06 - Fixation des nacelles, carénages ou capotages

Abrégé

The invention relates to a fire resistance device (50) that is designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of said turbomachine. According to the invention, the device (50) comprises two contacting lips (52a, 52b) which extend along different lines (72a, 72b), a first lip (52a) with a C-shaped section being integrated inside a contact structure (73), and a second lip (52b) having a protruding blocking portion (63) at the end thereof, protecting said contact structure (73).

Classes IPC  ?

• F02C 7/25 - Prévention ou protection contre l'incendie
• B64D 29/06 - Fixation des nacelles, carénages ou capotages
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
• F02C 7/28 - Agencement des dispositifs d'étanchéité

Abrégé

The invention relates to a turbomachine rotor blade which is characterized in that: - the ratio between the maximum thickness and the chord at 30% of the height of the blade is between 20% and 42% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at 70% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at 90% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at the blade head is between 3% and 21% of the ratio between the maximum thickness and the chord at the blade root.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

The invention relates to a turbomachine rotor blade comprising a plurality of blade sections stacked along an axis between a blade root and a blade head defining between them the height of the blade, each blade section comprising a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

The invention relates to a fan module (3) comprising variable-pitch blades, said fan module (3) including: a fan rotor (20) bearing the blades (23) of the fan (4, 400a, 400b), each mounted to pivot about a pitch axis (A); a fan shaft (21) extending along a longitudinal axis X inside the fan rotor and driving the fan rotor in rotation; a power shaft (11) driving the fan shaft in rotation by means of a planetary gear speed reducer (50); at least a first and a second bearing (69, 71) for guiding the rotation of the fan rotor, housed inside a lubrication chamber (60); and a system (32) for varying the pitch of the fan blades, comprising a connecting mechanism (33) connected to the blades of the fan and a control means (34) acting on the connecting mechanism (33). According to the invention, the first bearing (69) is disposed upstream of the speed reducer (50) and the second bearing (71) is disposed downstream of the speed reducer (50), the fan rotor (20) being connected to the fan shaft (21) by means of an annular trunnion (59) extending at least along an upstream portion of the lubrication chamber (60).

Classes IPC  ?

• F04D 25/02 - Ensembles comprenant des pompes et leurs moyens d'entraînement
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques
• F01D 5/12 - Aubes
• F01D 7/00 - Rotors à aubes réglables en marche; Leur commande
• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F01D 25/18 - Systèmes de lubrification
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02K 3/068 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux caractérisé par une longueur axiale courte par rapport au diamètre
• F04D 29/054 - Dispositions pour le raccordement ou l'assemblage des arbres
• F04D 29/056 - Paliers
• F04D 29/063 - Lubrification spécialement adaptée aux pompes pour fluides compressibles
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

The invention relates to an engine assembly (200) for an aircraft comprising a bypass turbomachine as well as a turbomachine attachment pylon (202) comprising an air-oil exchanger system (30) arranged in an inter-ducts compartment (22) between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling (20), the exchanger system being supplied with air from a secondary flow duct (14b) of the turbomachine delimited radially on the inside by the inter-ducts cowling (20), and the exchanger system (30) being supported by a support (34) arranged in the inter-ducts compartment (22), this support (34) being mechanically connected to the attachment pylon by connecting means (30) passing through the inter-ducts cowling (20).

Classes IPC  ?

• F01M 5/00 - Chauffage, refroidissement ou commande de la température du lubrifiant; Moyens de lubrification facilitant le démarrage du moteur
• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliers; Lubrification
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
• F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur
• F16N 39/02 - Dispositions pour conditionner des lubrifiants dans les circuits de lubrification par refroidissement

Abrégé

The invention concerns an air-sealing device (40) intended to be inserted between an aircraft dual-flow turbine engine casing element (16) and a nacelle element (30), the sealing device comprising an attachment tab (42) at the end of which is located a sealing portion (44) having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

Classes IPC  ?

• F02C 7/28 - Agencement des dispositifs d'étanchéité
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
• F16J 15/02 - Joints d'étanchéité entre surfaces immobiles entre elles

Abrégé

The method for detecting a rotating stall comprises; - a step (E90, E100) of determining a level of variation of a static pressure in a combustion chamber of the turbojet engine around an average value of this static pressure; - a step (E11) of comparing the level of variation of the static pressure relative to a first threshold (THR.1); - a step (E140) of comparing a temperature measured at the outlet of a turbine of the turbojet engine relative to a second threshold; and - if the level of variation of the static pressure is greater than the first threshold and the temperature at the outlet of the turbine is greater than the second threshold, a step (E170) of detecting the presence of a rotating stall.

Classes IPC  ?

• F04D 27/00 - Commande, p.ex. régulation, des pompes, des installations ou des systèmes de pompage spécialement adaptés aux fluides compressibles
• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant

Abrégé

The invention relates to a method for control of a cylinder (12), comprising the following steps: providing a cylinder that has a piston (22), a servo valve (14), and a measuring device (16) that comprises at least one first position sensor (28) and one second position sensor (30); taking position measurements (X1, X2) of the piston simultaneously with the first position sensor and with the second position sensor; determining at least one first travel speed (v1) of the piston on the basis of the position measurements of the piston taken with the first position sensor; determining at least one second travel speed (v2) of the piston on the basis of the position measurements of the piston taken with the second position sensor; and comparing each of the first and second determined travel speeds (v1, v2) of the piston with a modeled (vmod) or a predetermined travel speed of the piston so as to ascertain which is the more reliable position sensor.

Classes IPC  ?

• F15B 19/00 - Test des systèmes ou appareils de manœuvre utilisant la pression d'un fluide, dans la mesure où ils ne sont pas prévus ailleurs

Abrégé

The invention relates to a computing environment system for monitoring aircraft engines, said system being connected to a cluster of servers, said system comprising: - an application interface (13) configured so as to receive user codes (19) that are developed independently from a distributed deployment system specifying the calculation of a set of indicators relating to an aircraft engine (3) for deployment on a fleet (12) of aircraft engines; - an extraction module (15) configured so as to extract said indicators by deploying parallel calculations on temporal flight data from the fleet of aircraft engines and stored in a database (9) distributed over said cluster (5) of servers (7); - a learning module (17) configured so as to use said indicators to construct, without supervision, from said indicators, a monitoring model (21) representative of the indicators by implementing predetermined learning functions.

Classes IPC  ?

• G06F 8/60 - Déploiement de logiciel
• G06N 20/00 - Apprentissage automatique
• G05B 23/02 - Test ou contrôle électrique
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

Abrégé

The invention relates to a turbojet engine comprising a central shaft (AC) surrounded by a coaxial and independent high-pressure body (CH), said turbojet engine comprising, from upstream (AM) to downstream (AV): - a fan (13) driven by the central shaft (AC) ;- a high-pressure compressor (16) and a high-pressure turbine (17) supported by the high-pressure body (CH); - an inter-turbine housing (18); - a low-pressure turbine (19); and - an exhaust housing (21); said turbojet engine additionally comprising: - a low-pressure rotor (RB) which extends downstream of the central shaft (AC) and supports the low-pressure turbine (19); - a rotor bearing (23) supported by the exhaust housing (21); - a reduction gear (22) by means of which the low-pressure rotor (RB) drives the central shaft (AC), said reduction gear being located upstream of the rotor bearing (23); and - a downstream shaft bearing (29) which is located upstream of the reduction gear (22).

Classes IPC  ?

• F02C 7/06 - Aménagement des paliers; Lubrification
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant

Abrégé

The invention relates to a dual-flow turbojet engine having a central shaft (AC) surrounded by a high-pressure body (CH) which rotate about the same longitudinal axis (AX) while being independent in rotation, and comprising: - a fan (13) driven by the central pressure shaft; - a high-pressure compressor (16) and a high-pressure turbine (17) mounted on the high-pressure body (CH); - an inter-turbine casing (18); - a low-pressure turbine (19) mounted on a low-pressure rotor (RB) surrounding the central shaft (AC); - an exhaust casing (21) on which an output cone (23) is mounted; -a reduction gear (22) by means of which the low-pressure rotor (RB) drives the central pressure shaft (AC); - two bearings (34) mounted on the exhaust casing (21) and respectively receiving the central shaft (AC) and the low-pressure rotor (RB); and - a bearing (26) mounted on the inter-turbine casing (18) and receiving the low-pressure rotor (RB).

Classes IPC  ?

• F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance

Abrégé

The invention relates to a turbojet engine including a shaft surrounded by a low-pressure rotor surrounded by a coaxial and independent high-pressure spool, this turbojet engine including from upstream to downstream:- a fan driven by the shaft;- a low-pressure compressor carried by the rotor;- an inter-compressor casing;- a high-pressure compressor and a high-pressure turbine carried by the high-pressure spool;- an inter-turbine casing;- a low-pressure turbine carried by the rotor;- an exhaust casing;this turbojet engine including:- an upstream rotor bearing carried by the inter-compressor casing;- a downstream rotor bearing carried by the exhaust casing;-a gearbox downstream of the downstream bearing and through which the rotor drives the shaft;- a downstream shaft bearing downstream of the downstream rotor bearing.

Classes IPC  ?

• F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance

Abrégé

The invention relates to a seal (20) configured to be mounted on a first member of a turbomachine (100), such as a door (16) of a discharge valve (10), and to come to bear against a second member (11, 12, 128) of the turbomachine, such as a hub (11) of an intermediate casing (12), said seal being characterized in that it comprises: latching means (21) for mounting said seal on said first member; a sealing lip (24) that seals with respect to air by contact and that is intended to come to bear against said second member (11, 12, 128); means (23) for preventing said sealing lip (24) from being turned back, increasing the stiffness of the seal (20) at the base of the sealing lip (24).

Classes IPC  ?

• B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
• F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
• F02C 7/28 - Agencement des dispositifs d'étanchéité
• F16J 15/02 - Joints d'étanchéité entre surfaces immobiles entre elles

Abrégé

The invention relates to a propulsion system (10) intended to be mounted on an aircraft comprising a main body, said propulsion system (10) comprising: - a first rotating propulsive member (11) and a second rotating propulsive member (12) that are intended to be mounted on either side of said main body, - a transmission housing (3) connected to the first rotating propulsive member (11) via a first mechanical shaft (51) and to the second rotating propulsive member (12) via a second mechanical shaft (52), - a single gas generator (2) connected to said transmission housing (3) and configured to rotate the first rotating propulsive member (11) and the second rotating propulsive member (12), and - a single auxiliary turbomachine (4) configured to rotate the first rotating propulsive member (11) and the second rotating propulsive member (12) independently of the gas generator (2).

Classes IPC  ?

• B64D 35/04 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors
• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz

Abrégé

The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur

Abrégé

The invention relates to a device for monitoring the lifetime of at least one hydraulic apparatus of an aircraft that is subject to variations in hydraulic pressure during flight, comprising an interface for receiving measurement data which are representative of hydraulic pressure (P). The invention is characterised in that the device comprises a processing device, comprising a means for detecting a pressure (P) load (SOLLEND) of a damaging nature, which load is defined by the fact that the pressure (P) comprises a pressure increase (?PAUG) that is greater than a predetermined damage threshold (S?P), followed by a pressure decrease (?PDIM) that is greater than the threshold (S?P), a means for calculating a pressure variation magnitude that is equal to the maximum increase (?PAUG) and the maximum decrease (?PDIM), a means for projecting the magnitude onto a decreasing curve or straight line of a damage model in order to determine the permissible number of loads corresponding to the magnitude, a means for calculating a potential damage ratio that is equal to a number of reference loads divided by the permissible number, a means for increasing a count of accumulated ratios by said ratio.

Classes IPC  ?

• G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
• G01M 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
• F28D 1/047 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source d avec des canalisations d'échange de chaleur immergées dans la masse du fluide avec canalisations tubulaires les canalisations étant courbées, p.ex. en serpentin ou en zigzag
• F28D 15/00 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations
• F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
• F28F 1/12 - Eléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p.ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire
• G05B 23/02 - Test ou contrôle électrique

Abrégé

The invention relates to a turbine shroud sector (2) made of ceramic matrix composite, of longitudinal axis X and which comprises a base (3) with a radially internal face (6), a radially external face (7) from which there extend upstream (4) and downstream (5) tabs for attachment to a shroud support structure, and at least one inter-sector lateral face (9), the base comprising a first slot (10) and a second slot (16), which is arranged radially on the outside of the first slot, which slots are each formed in the lateral face, a first and a second sealing strip (14, 17) respectively resting against a radially internal wall of these first and second slots. According to the invention, the first strip has the overall shape of an omega and the shroud sector exhibits a first clearance which is defined radially between a central part (14a) of the first strip and the radially internal wall of the first slot, and a second clearance which is defined radially between this central part and a radially external wall (15b) of the first slot.

Classes IPC  ?

• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator

Abrégé

The invention concerns an aircraft turbomachine comprising an outer housing (2) delimiting, with an inner hub (3), a flow path (1) for a gas stream in which a low-pressure turbine is arranged, configured to rotate a low-pressure shaft; the turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream from the first propeller, the first propeller (31) being rotated by the low-pressure shaft and the second propeller being rotated by an electric motor (70), the second propeller (32) further being arranged at a distance of between 1.5 and 4 chord lengths (LC1) from the first propeller (31) defined between the respective pitch axes (A31, A32) of each of the first and second propellers.

Classes IPC  ?

• F02K 3/072 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comportant des rotors contra-rotatifs
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

A method for controlling a turbomachine (T) comprising an electric motor (ME) forming a torque injection device on a high-pressure rotation shaft (22), in which method a fuel flow setpoint QCMD and a torque setpoint TRQCMD provided at the electric motor (ME) are determined, the control method comprising: a step of implementing a first fuel control loop in order to determine the fuel flow set point QCMD, a step of implementing a second, torque control loop in order to determine the torque setpoint TRQCMD comprising i. a step of determining a torque correction variable ?TRQCMD as a function of a transitory speed setpoint NHTrajAccelCons, NHTrajDecelCons and ii. a step of determining the torque setpoint TRQCMD as a function of the torque correction variable ?TRQCMD.

Classes IPC  ?

• F02C 9/48 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel
• F01D 15/00 - Adaptations des "machines" ou machines motrices à des usages particuliers; Combinaisons des machines motrices avec les dispositifs qu'elles entraînent
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant

Abrégé

The invention relates to a profiled structure which is elongated in a direction in which the structure has a length exposed to an air flow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in the direction of elongation, clamps (28a) defined by successive teeth (30) and recesses (32). Along the profiled leading edge and/or trailing edge, the successive teeth (30) and recesses (32) extend over only a portion of the length exposed to the flow, over which portion the amplitude and/or spacing of the teeth varies monotonously with the exception of the few teeth closest to each end of said portion, a remaining portion (280) of said length being smooth.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• B64C 3/14 - Profil de la surface portante
• B64C 11/18 - Caractéristiques aérodynamiques
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

Disclosed is a positioning tool (22) for an endoscopic inspection means for inspecting a manifold casing (12) of an aircraft turbine engine (10), this manifold casing comprising an annular wall (14) with an axis of rotation A that comprises through holes (16) and that is surrounded by an annular manifold (18) comprising at least one gas port (20a, 20b) emerging in an annular recess (21) delimited between the manifold and the wall, characterised in that the tool comprises: - a centring device (24) configured to be engaged in the port and comprising a distal end (24a) configured to bear against the wall, and a proximal end (24b) configured to be held securely on an opening (26) of the port, and - at least one mask (28a, 28b, 28c) configured to be engaged in the port and to be positioned and secured on the centring device, this mask comprising an endoscopic inspection window (30, 30', 30'') for inspecting a zone (Z) to be inspected inside the port and/or the recess.

Classes IPC  ?

• G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
• G01D 11/30 - Supports spécialement adaptés à un instrument; Supports spécialement adaptés à un ensemble d'instruments

Abrégé

The invention concerns a suspension assembly (7) for a turbine engine, comprising a beam (10) intended to be attached to a pylon of an aircraft, and a cylindrical part (15) hinged to a ball-joint housing, the ball-joint housing comprising a body (11), and a ball-joint yoke (16) hinged to the body (11), the cylindrical part (15) being mounted so as to be able to pivot about its axis in the ball-joint yoke, characterised in that the cylindrical part (15) is intended to be secured to a fixed part (8) of the turbine engine (1), the body (11) of the ball-joint housing being secured to the beam (10).

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).