Abrégé

The present invention relates to an aircraft turbomachine (10) with a recuperation cycle, comprising: - a heat exchanger (6) comprising a first circuit (62) with an inlet (622) connected to an outlet (444) of a flow path (44) of a turbine (4), and a second circuit (64) with an inlet (642) connected to an air bleed system (20), and an air outlet (644), - at least one duct (7) for passing services (S) extending from a turbine casing (40) to a bearing housing (5), and - an air circulation device (8) comprising a first channel (82) with a first upstream end (822) connected to the system (20) and a first downstream end (824) connected to the inlet (642) and a second channel (84) having a second downstream end (844) connected to the outlet (644), and wherein the duct (7) extends radially outwards as far as the device (8).

Classes IPC  ?

• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement

Abrégé

Device (210) for measuring a rotational speed of an aircraft propeller (211), comprising: - an optical speed sensor (220); - an optical fiber (230) connected to the optical speed sensor and intended to be connected to a control unit of the aircraft; and - at least one target (251, 252) configured to follow the rotation of the propeller, the optical speed sensor being configured to detect the target.

Classes IPC  ?

• G01P 3/481 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions
• B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
• B64C 11/50 - Synchronisation des hélices multiples
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts

Abrégé

The present application relates to a method for calibrating a model for estimating a torque supplied by an electric machine (10), which comprises the following steps: (E1) measuring an electric current in the electric machine (10) for an operating point; (E2) estimating the torque supplied by the electric machine (10) for the operating point from the measured electric current and an estimation model which associates an output torque with an input electric current; (E3) measuring a reference torque provided by the electric machine (10) for the operating point; (E4) comparing the estimated torque with the reference torque; and (E5) adjusting the estimation model so as to reduce, or even cancel, a difference between the estimated torque and the reference torque.

Classes IPC  ?

• G01M 15/00 - Test des moteurs
• H02P 21/20 - Estimation du couple
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• G01R 31/34 - Tests de machines dynamoélectriques

Abrégé

This method for managing the output of a specific-consumption mode of an aircraft comprises a step of identifying a need to reactivate a turbine engine in the nominal mode of said turbine engine, and a step of: - normal reactivation of the turbine engine in the nominal mode for the turbine engine for a first duration when a first condition (C1) is met (step 10); - accelerated reactivation of the turbine engine in the nominal mode for the turbine engine for a second duration when a second condition (C2) is met (step 12); - rapid reactivation of the turbine engine in the nominal mode of the turbine engine for a third duration when a third condition (C3) is met (step 14), the first duration being longer than the second duration, and the second duration being longer than the third duration.

Classes IPC  ?

• F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage

Abrégé

The invention relates to a method for assisting with propulsion by detecting a failure of a turboshaft engine of an aircraft operating in a nominal mode, the aircraft comprising a deactivated assistance motor, which method comprises a step (2) of comparing operating parameters of the turboshaft engine with the equivalent parameters of a model representative of a healthy turboshaft engine, a step (4) of detecting a failure of the turboshaft engine by detecting an anomaly in at least one operating parameter of the turboshaft engine, a step (6) of selecting an activation mode for the assistance motor on the basis of the operating parameters of the turboshaft engine and/or of flight parameters of the aircraft, and a step (8) of activating the assistance motor with the selected activation mode.

Classes IPC  ?

• F01D 13/00 - Combinaisons de plusieurs "machines" ou machines motrices
• B64C 27/12 - Entraînements des rotors
• F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage

Abrégé

The invention relates to an aircraft turbine engine (10) having: - a compressor (14), - an annular combustion chamber (24), - a system (32) for diffusing and straightening an air stream exiting the compressor in order to supply the combustion chamber, and - a heat exchanger (38), this heat exchanger having: + a first circuit (38a) supplied with exhaust gas from the turbine engine, and + a second circuit (38b) comprising an inlet (38ba) connected by a first scroll (40a) to an outlet (34b) of the diffuser (34), and an outlet (38bb) connected by a second scroll (40b) to an inlet (36a) of the straightener (36), the scrolls (40a, 40b) comprising connecting arms (82, 84) that rigidly connect the annular portions (86, 88, 94) of the scrolls which are secured or connected to the diffuser (34) and to the straightener (36), respectively. Figure for the abstract: Figure 5

Classes IPC  ?

• F02C 3/09 - 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 comprenant au moins un étage radial du type centripète
• F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement
• F04D 29/44 - Moyens de guidage du fluide, p.ex. diffuseurs
• F04D 29/58 - Refroidissement; Chauffage; Réduction du transfert de chaleur

Abrégé

The invention relates to a turboprop (10) comprising: - a turbine (12) mechanically connected to an input (21) of a reducer (20); - a tail shaft (30) bearing a variable-pitch propeller (31); - a rotary electric machine (46); and - an electric oil pump (40) configured to supply a hydraulic circuit (33) for adjusting the pitch of the propeller (31), wherein the electric oil pump (40) is configured to supply a lubrication circuit (53) for lubricating the bearings (25) of the reducer (20).

Classes IPC  ?

• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 17/26 - Dispositifs utilisant des éléments sensibles ou des organes de commande terminaux ou les organes de liaison entre les deux, p.ex. commande assistée l'énergie de fonctionnement ou de puissance assistée étant essentiellement non mécanique à fluide, p.ex. hydraulique
• 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
• F01D 25/18 - Systèmes de lubrification
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
• B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
• F02C 9/58 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance avec la commande d'une hélice à pas variable

Abrégé

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), which comprises: - calculating, for each damage counter (FC, EF), a maximum incrementation rate (dC_FC_max, dC_EF_max) of the counter (FC, EF) so that the counter (FC, EF) remains below a predefined threshold (C_FC_max, C_EF_max) throughout a target service life (DDV_cible); - calculating, on the basis of one or more thresholds (NGmax FC, NGmax EF, T4xmax_EF) of at least one parameter (NG, T4x), at least one limit (PEinf, PEsup) of an operating variable of the turboshaft engine (TM) which must not be exceeded so that the incrementation rate (dC_FC, dC_EF) of the counter (FC, EF) remains below the maximum incrementation rate (dC_FC_max, dC_EF_max); and - transmitting a current value and the limit (PEinf, PEsup) of the operating variable to a display device (AF) of the aircraft (100).

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
• G01M 15/05 - Test des moteurs à combustion interne par contrôle combiné d'au moins deux paramètres différents des moteurs
• G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
• G05B 23/02 - Test ou contrôle électrique

Abrégé

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric machine (30, 40) and a second electric machine (32, 42) that is less powerful than the first electric machine, one of the electric machines being coupled to the gas generator (12, 22) to rotate the gas generator during a starting phase, and being coupled to the free turbine (11, 21) after the starting phase to generate electric energy, the other of the electric machines being coupled to the gas generator (12, 22) only, at least one of the first and second electric machines of the first engine (1) and/or the second engine (2) being able to transmit electric energy to the other electric machine.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/26 - Démarrage; Allumage
• F02C 3/113 - 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 aves des transmissions de puissance variables entre les rotors

Abrégé

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbines (11, 21) of the first and second engines (1, 2), the first engine (1) comprising a first electric machine (30) and a second electric machine (32) that is less powerful than the first electric machine (30), one of the first and second electric machines (30, 32) being able to be coupled to the gas generator (12) and to rotate the gas generator during a starting phase of the engine, and also being able to be coupled to the free turbine (11) in order to generated electric energy after the starting phase, the other of the first and second electric machines being coupled to the gas generator (12) only.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/26 - Démarrage; Allumage
• F02C 3/113 - 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 aves des transmissions de puissance variables entre les rotors

Abrégé

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), comprising: - computing a margin of a parameter (NG, T4x) of a thermal chain (TH), this margin being taken as margin (PMD1, PMT1) of the thermal chain (TH); - computing a margin of a parameter (IBAT) of an electrical chain (ELEC), at least part of this margin being taken as margin of the electrical chain (ELEC); - adding together the margin (PMD1, PMT1) of the thermal chain (TH) and the margin of the electrical chain (ELEC) so as to obtain a total margin (ePMD) of the propulsion system (102); and - transmitting the total margin (ePMD) to a display device (AF) in the aircraft (100) so that the display device (AF) displays the total margin (ePMD).

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

Abrégé

The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11) forming part of a transmission gearbox (12) which is positioned axially at a front end (13) of the propulsion system (2); - first and second electric machines (14, 15) mechanically and respectively connected to the high-pressure and low-pressure spools (4, 5), the electric machines (14, 15) being configured to operate in modes referred to as motor and generator, the first and second electric machines (14, 15) being fixed to the transmission gearbox (12); - a control system (16) which is configured to allow the transfer of power between the high-pressure and low-pressure spools (4, 5) via the first and second electric machines (14, 15).

Classes IPC  ?

• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• B64C 27/12 - Entraînements des rotors
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• 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
• 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
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

The invention relates to an electric machine for an aircraft, comprising a stator (1) comprising at least three phases (10) each comprising a winding (12), a control branch (11) and a neutral branch (13), the neutral branches (13) being connected together at a neutral point (14), the electric machine (3) comprising at least one protection member (5) mounted on the neutral branch (13) of at least one phase (10), each protection member (5) comprising: an inactive state (P1), in which the protection member (5) allows the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, and a protection state (P2), in which the protection member (5) interrupts the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, so as to protect the electric machine in the event of a short circuit (CC).

Classes IPC  ?

• H02H 3/08 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à une surcharge
• H02H 7/08 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour moteurs dynamo-électriques

Abrégé

Propulsion assembly (100) for an aircraft, in particular a multi-engine helicopter, comprising at least a first engine (1) and a second engine (2) that are configured to operate in at least one standby mode, a primary air-circulation device (30) configured to bleed air from the first engine (1) via a first bleed channel (310) and/or from the second engine (2) via a second bleed channel (320) in order to convey it to equipment of the propulsion assembly (100), and a secondary air-circulation device (40) configured, when one of the first or the second engine (1, 2) operates in standby mode, to bleed air from the other of the first or the second engine (1, 2) not operating in standby mode and to convey it to the one of the first or the second engine (1, 2) operating in standby mode.

Classes IPC  ?

• B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
• 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 method for assembling a first metal part (21) to a second metal part (22), the first and second metal parts having different sizes, the method comprising the following operations: - a) producing (110) a slot (23) in a surface of the first metal part (22); - b) positioning (120) the second metal part (22) in line with the slot (23) of the first metal part; and - c) welding (130) the second metal part (22) to the first metal part (21) through the slot (23) using a high-energy welding beam, the slot guiding the welding beam. The invention also relates to a centrifugal diffuser for turbomachinery comprising a metal cover (21) and a plurality of metal blades (22), each blade (22) being assembled with the cover (21) by means of the method hereinbefore.

Classes IPC  ?

• F04D 29/44 - Moyens de guidage du fluide, p.ex. diffuseurs
• F04D 29/60 - Montage; Assemblage; Démontage
• B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
• F04D 29/62 - Montage; Assemblage; Démontage des pompes radiales ou hélicocentrifuges
• F04D 29/02 - Emploi de matériaux spécifiés
• B23K 15/00 - Soudage ou découpage par faisceau d'électrons
• B23K 26/00 - Travail par rayon laser, p.ex. soudage, découpage ou perçage 

Abrégé

The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interior volume so as to form an air passage (40) between the insert (30) and the external enclosure (10); and at least one breakable joining part (20) connected to the insert (30) on one side and to the external enclosure (10) on the other side; wherein at least one of the mechanical breaking strength of the breakable joining part (20), the mechanical breaking strength between the breakable joining part (20) and the external enclosure (10) and the mechanical breaking strength between the breakable joining part (20) and the insert (30) is lower than the mechanical breaking strength of the external enclosure (10) and the mechanical breaking strength of the insert (30).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue

Abrégé

One aspect of the invention relates to a method for dimensionally inspecting at least one component manufactured by means of an additive manufacturing machine, the step of additive manufacturing being carried out by successive depositions of a powder bed and by fusing the powder bed after each deposition, the method comprising the steps of: - acquiring an image of the component being manufactured after at least one step of depositing and fusing the powder bed; - comparing the image with an image of a reference template; - verifying the dimensional conformity of the component on the basis of the comparison.

Classes IPC  ?

• G06T 7/00 - Analyse d'image

Abrégé

The invention relates to a synchronous electric machine (10) for aircraft, which comprises a stator (13) and a wound rotor (38) inserted into the stator, the stator comprising two sets of stator coils (47, 49) intended to be connected to different power converters, and the wound rotor comprising a rotor shaft (11) and two rotor coils (39, 40) each intended to be supplied with a different supply current. The two sets of stator coils are arranged in the stator in such a way that when a first set of stator coils (47) fails, the second set of stator coils (49) cooperates with at least the second rotor coil (40) supplied with the associated supply current in order to generate a mechanical torque on the rotor shaft, and so that the power converter connected to the first set of stator coils does not deliver any electrical power.

Classes IPC  ?

• H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
• H02K 16/00 - Machines avec plus d'un rotor ou d'un stator
• H02P 25/022 - Moteurs synchrones
• H02K 19/12 - Moteurs synchrones pour courant polyphasé caractérisés par la disposition des enroulements d'excitation, p.ex. pour auto-excitation, compoundage ou changement du nombre de pôles
• H02K 19/26 - Génératrices synchrones caractérisées par la disposition des bobinages d'excitation

Abrégé

The invention relates to a hybrid electrical architecture (101) for an aircraft (103) which comprises a turbomachine (107) and a reduction gearbox (111) intended to rotate at least one propulsion member (105) of the aircraft (103). The architecture (101) also comprises at least one low-voltage electrical network (113) with at least one low-voltage electric machine (117, 118) mounted on the reduction gearbox (111) or on the turbomachine (107) and a high-voltage electrical network (125) with high-voltage electric machines (129) mounted on the turbomachine (107).

Classes IPC  ?

• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• H02J 1/08 - Systèmes à trois fils; Systèmes ayant plus de trois fils
• H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée

Abrégé

The invention relates to a collector (10) for a drained liquid for a turbine engine, comprising: - an internal cavity (54) comprising a first space (54A) for collecting the liquid and a second space (54B) for transferring the liquid, the internal cavity extending longitudinally along a first direction (Z) between a first end closed by a bottom wall (16) of the collector and a second end closed by a cover (14); and - at least one inlet (44) for the drained liquid; the first and second spaces being separated by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space; wherein the means (58) for restricting the passage of the drained liquid is mounted such that it can be removed from the collector by moving it in the direction from the bottom wall to the cover of the collector.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01D 25/32 - Recueil de l'eau de condensation; Drainage
• F01M 11/04 - Remplissage ou vidange du lubrifiant des "machines" ou moteurs

Abrégé

The invention relates to a collector (10) for a drained liquid for an aircraft turbine engine, said collector comprising: - an internal cavity (54) comprising a first space (54A) for collecting the drained liquid and a second space (54B) for transferring the collected liquid to a recovery outlet (30); - at least one inlet (44) for the drained liquid, in fluid communication with the first space; and - at least one recovery outlet in fluid communication with the second space; wherein the first space and the second space are separated from each other by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space, the air in the first space being in communication with the air in the second second space such that the air pressure in the first and second spaces is identical.

Classes IPC  ?

• F01D 25/32 - Recueil de l'eau de condensation; Drainage
• F01D 25/18 - Systèmes de lubrification

Abrégé

The invention relates to an assembly for an aircraft turbomachine (20), the assembly comprising a stator section (26), a first bearing (28a), a second bearing (28b) and a holder part (32) in an oil chamber (22) delimited by an outer chamber-delimiting portion (24) incorporated into the stator section (26), the holder part (32) comprising: - a first axial end portion (34a) forming an outer ring (36) of the first bearing (28a) or supporting such a ring (36); - a second axial end portion (34b) forming an outer ring of the second bearing (28b) or supporting such a ring, an oil squeeze film damper (50) being arranged between the second portion (34b) and the stator section (26); - an intermediate ring (46) arranged axially between the first and second portions (34a, 34b) and forming a flexible connection and an oil-splash protection element.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators

Abrégé

The invention relates to a turbine engine module, in particular an aircraft turbine engine (10), comprising: - an annular casing (52) having an internal wall (53) forming a channel wall; and - a nozzle (32) surrounded by the casing and comprising an annular external platform (36) and an annular internal platform (37) between which stator blades (34) extend, the external platform having an external face (36b) that faces the internal wall of the casing and comprises an annular groove (60) oriented towards the outside and housing a sealing device (64), the sealing device coming into cylindrical contact with a track (66) of the internal wall (53) of the casing, the module being characterised in that the internal wall (53) of the casing comprises a thermal barrier (70) made of ceramic material directly above the track (66), the track being arranged between the thermal barrier and the sealing device.

Classes IPC  ?

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

Abrégé

The invention relates to a turbomachine (100) for a hybrid aircraft, the turbomachine comprising a gas generator (12) carried by a generator shaft (14), at least one free turbine (11) carried by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), a main rotor (60), and at least one reversible electric machine (30), the turbine shaft (13) being a through-shaft and extending axially between a first end engaged with the electric machine (30) and a second end engaged with the main rotor (60).

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 3/14 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail caractérisés par l'aménagement de la chambre de combustion dans l'ensemble

Abrégé

The invention relates to an aircraft turbomachine (10) comprising: a gas generator (12) comprising an output shaft (26) as well as a first lubricating circuit (28); and equipment (14) coupled to the output shaft (26) and comprising a rotor (38) which is rotationally guided by at least one rolling bearing (40), the equipment (14) comprising a second lubricating circuit (46) which is independent of the first lubricating circuit (28) and which is configured to lubricate the rolling bearing (40), the equipment further comprising a system (50) for cooling the rolling bearing (40), the cooling system (50) being configured to circulate oil in the region of at least one ring (40b) of the rolling bearing, characterized in that the cooling system (50) is independent of the second lubricating circuit (46) and is connected to the first lubricating circuit (28).

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliers; Lubrification
• F01D 25/12 - Refroidissement
• F16C 37/00 - Refroidissement des paliers

Abrégé

A propulsive assembly (100) for a multi-engine hybrid aircraft, comprising a first and a second gas turbine (10, 20) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21) via a first and a second main coupling means (51, 52), a first and a second reversible electric machine (30, 40) each coupled to the gas generator (12, 22) via a first deactivatable coupling means (31, 41), and each coupled to the main rotor (62) via a second deactivatable coupling means (32, 42), the first deactivatable coupling means (31, 41) being activated when the electric machines (30, 40) rotate in a first direction of rotation, and the second deactivatable coupling means (32, 42) being activated when the electric machines (30, 40) rotate in a second direction of rotation opposite to the first direction of rotation.

Classes IPC  ?

• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• 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
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

One aspect of the invention relates to a filtering device (10) for a turbomachine, the device comprising: - a filter support (14); - a removable filter (18) co-operating with the filter support; - a cover (12); - an indicator pin (16); the device comprising a plate (13) that is translatably movable relative to the cover and relative to the indicator pin, the plate being translatably movable between two positions: - a first position such that the plate bears against the removable filter and the indicator pin is in a retracted position; - a second position such that the plate is remote from the cover due to the absence of the removable filter and the indicator pin is in an extended position.

Classes IPC  ?

• B01D 35/143 - Indicateurs de l'état du filtre

Abrégé

The invention relates to a turboshaft engine (1) for an aircraft (2) comprising: - a gas generator (3) comprising a compressor (4), a combustion chamber (5) and an expansion turbine (6); - a power turbine (8) rotating a power take-off (9) by means of a reduction gear (10); - a heat exchanger (11) comprising a first circuit (12) and a second circuit (17); characterised in that the compressor (4) comprises a first shaft (22) rotated by a second shaft (23) of the expansion turbine (6) by means of a transmission mechanism (24), the transmission mechanism (24) and the reduction gear (10) forming part of a gearbox (25) which is arranged axially at a front end (20) of the turboshaft engine (1), such that the compressor (4) is arranged axially between the gearbox (25) and the power turbine (8). Drawing_references_to_be_translated

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
• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• 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 DC-to-DC converter (209) for an electrical aircraft propulsion system designed to be connected in series with an electrical energy storage unit of the electrical propulsion system. The DC-to-DC converter (209) comprises an inverter (401), a transformer (403) and a rectifier (405), and further comprises a current source (417) that is connected to the rectifier (405) and is configured to control the power passing through the DC-to-DC converter (209). The transformer (403) comprises a primary (403a) and two secondaries (403b, 403c), the two secondaries (403b, 403c) sharing a common terminal (407) designed to be connected to a high-voltage DC bus (207) of the electrical propulsion system (201) and two other terminals (409, 411) that are connected to the rectifier (405). The rectifier (405) comprises two arms comprising at least two transistors (415a, 415b, 415c, 415d) that are each in series and are connected, on the one hand, to the two other terminals (409, 411) of the transformer (403) and, on the other hand, to the current source (417).

Classes IPC  ?

• H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• H02M 7/219 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs dans une configuration en pont

Abrégé

An aircraft turbomachine (10) having a gas generator (12) comprising, along a longitudinal axis (X), at least one compressor (14), a combustion chamber (16) and at least one turbine (18), the turbomachine (10) further having at least one duct (20) for supplying liquid to at least one member chosen from an oil jet (22) and a fuel injector (50), this duct (20) having rectilinear portions (21a, 21b) and bent portions (21c, 21d) and comprising at least one region in which the liquid is liable to coke, characterized in that it comprises at least one turbulence element (40-48) in the at least one region in the duct.

Classes IPC  ?

• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/18 - Systèmes de lubrification
• F02C 7/22 - Systèmes d'alimentation en combustible
• F16L 55/24 - Prévention de l'accumulation de résidus ou autres matières dans les tuyaux, p.ex. par purgeur, par crépine
• B08B 9/032 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau

Abrégé

The invention relates to a method for regulating the speed of a propulsion device of a hybrid propulsion unit for an aircraft comprising: the propulsion device and an MGB; the heat engine and at least one electric motor, mounted in parallel on the MGB, the heat engine being provided with a fuel circuit; main and backup regulation systems for the heat engine, and a regulation system for the electric motor, each being capable of regulating the speed of the heat engine or the electric motor, respectively; and an aircraft control system, capable of sending a speed or power setpoint to each of the regulation means for the heat engine and the electric motor. The method comprises, when the main regulation system for the heat engine fails and is locked to a QCarbP* fuel flow command: - sending a speed setpoint NM2réf to the regulation system for the electric motor, the regulation system for the electric motor sending a power setpoint PM2* to the electric motor, whereby an instantaneous power PM2m of the electric motor is obtained; - simultaneously, sending a speed or power setpoint to the backup regulation system for the heat engine, the backup regulation system sending a fuel flow command QCarbAux* to the fuel circuit of the heat engine, which command is selected to vary the fuel flow QCarb injected into a combustion chamber of the heat engine according to whether the power PM1 of the heat engine is to be varied.

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors

Abrégé

The invention relates to a method for checking the maximum power available to members of a propulsion system of an aircraft (1) comprising first members (M1.1, M2.1, D10, TG, BAT1) that are sized to compensate for the failure of second members of the propulsion system (M1.2, M2.2, D20, TG, BAT2) by delivering a maximum power to keep the aircraft in a safe operating range, the method comprising the following steps for each of the first members: - placing the first member in a state that is substantially equal to a maximum power state (PM); - adjusting the power delivered by the second member working in synergy with the first member so that the first member and the second member contribute to delivering the power required for the aircraft in the flight phase; - determining the power delivered by the first member placed in the maximum power state; - from the determined power, deducing information relating to the maximum power available to the first member.

Classes IPC  ?

• B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts

Abrégé

The invention relates to a control device (30) for controlling an airflow guiding system (20), comprising: - at least one vane (21) that is rotatable on a shaft (21a) of the vane between a first angle and a second angle; - an actuator (31) comprising a body (32) inside which a piston (32a) is translatably mounted, the piston being rigidly connected to a drive rod (33); - a control rod (34) comprising a downstream end (34a) that is connected to the shaft (21a) of the vane, the actuator (31) being configured to drive the piston (32a) between a first end position (P1') and a second end position (P2') of a nominal operating range and the downstream end (34a) of the control rod (34) between a first end position (P1) and a second end position (P2) of a nominal operating range in which the vane (21) is movable between a first angle and a second angle, the device being characterised in that it comprises a drive mechanism (40) that connects an upstream end (33a) of the drive rod (33) to an upstream end (34b) of the control rod (34), which is opposite the downstream end (34a), and in that the drive mechanism (40) is configured so that, in the event of the control device failing, it places the downstream end (34a) of the control rod (34) in a safety position (PS) located between the first end position (P1) and a second end position (P2) of the nominal operating range and in which the vane (21) is oriented at a safety pitch angle between the first angle and the second angle.

Classes IPC  ?

• F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
• F01D 17/20 - Dispositifs utilisant des éléments sensibles ou des organes de commande terminaux ou les organes de liaison entre les deux, p.ex. commande assistée
• F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables

Abrégé

The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4% aluminium, at least 3.9% molybdenum, at least 3% titanium, at most 0.5% iron, at least 0.012% boron, at most 0.060% zirconium, at most 0.150% manganese, at most 0.2% silicon, at most 0.1% copper, at most 0.5 ppm bismuth, at most 5 ppm silver, at most 5 ppm lead, at most 25 ppm sulphur, at most 200 ppm oxygen, and at most 60 ppm nitrogen.

Classes IPC  ?

• B22F 1/05 - Poudres métalliques caractérisées par la dimension ou la surface spécifique des particules
• B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
• B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
• B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 10/36 - Commande ou régulation des opérations des paramètres du faisceau d’énergie
• B22F 10/366 - Paramètres de balayage, p.ex. distance d’éclosion ou stratégie de balayage
• B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 40/20 - Posttraitement, p.ex. durcissement, revêtement ou polissage
• B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
• B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
• C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
• C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
• F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion

Abrégé

The invention relates to a system (1) for automatically validating the response compliance of a penetrant testing line by analysing a reference test specimen undergoing dye penetrant testing from said penetrant testing line, the system comprising a casing (2) surrounding all the elements of the system (1), a positioning base (3) for the reference test specimen undergoing dye penetrant testing, at least two ultraviolet lighting devices (4) positioned on either side of the positioning base (3) so as to be able to illuminate it with ultraviolet light, an electronic board, a motorised linear guide (6) controlled by the electronic board and suitable for being able to move the positioning base (3) and hold said base in position in the casing (2), and a monochrome camera (10) having a lens directed towards the positioning base (3).

Classes IPC  ?

• G01N 21/91 - Recherche de la présence de criques, de défauts ou de souillures en utilisant la pénétration de colorants, p.ex. de l'encre fluorescente

Abrégé

The invention relates to a method for the quantitative measurement of an element (4) in a metal test specimen (1) which has received a thermochemical surface treatment, characterised in that the method comprises the following steps: • - a- making a cut in the test specimen; • - b- taking a photograph, using an optical microscope, of said cut on a surface S with magnification; • - c- calculating the ratio of the surfaces s occupied by the element with respect to the surface S in the photograph by means of an image-processing tool; and • - d- obtaining the content of the element in the surface S of the test specimen. A profile of the content of undesirable elements can thus be obtained without the subjective aspect of human checking, which profile is representative of a content obtained by acquiring diffraction of X-rays produced using a synchrotron.

Classes IPC  ?

• G01N 21/94 - Recherche de souillures, p.ex. de poussières
• G01N 21/95 - Recherche de la présence de criques, de défauts ou de souillures caractérisée par le matériau ou la forme de l'objet à analyser
• G06T 7/62 - Analyse des attributs géométriques de la superficie, du périmètre, du diamètre ou du volume
• G06T 7/00 - Analyse d'image
• G01N 1/28 - Préparation d'échantillons pour l'analyse
• G01N 33/204 - Leur structure, p.ex. structure cristalline

Abrégé

The invention relates to a dihydrogen injection device (2) having a longitudinal axis (X), intended to be mounted on an annular base of an annular combustion chamber (4) of a turbomachine, comprising an inner channel (6) for circulating dihydrogen, and an annular outer channel (8) for circulating a mixture at least comprising air, the inner channel (6) and the annular outer channel (8) being coaxial, an inner swirler (14) being provided in the inner channel (6) and an outer swirler (28) being provided in the annular outer channel (8), a downstream end (16) of the inner channel (6) being arranged upstream, at a distance r, from a downstream end (24) of the annular outer channel (8). Such combustion of dihydrogen makes it possible to eliminate carbon-containing polluting emissions such as carbon monoxide, unburned hydrocarbons or fine particles and smoke particles.

Classes IPC  ?

• F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
• F23D 14/48 - Buses
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23D 14/24 - Brûleurs à gaz sans prémélangeur, c. à d. dans lesquels le combustible gazeux est mélangé à l'air de combustion à l'arrivée dans la zone de combustion avec des conduits d'alimentation en air et en gaz séparés, p.ex. avec des conduits disposés parallèlement ou se croisant au moins un des fluides étant soumis à un mouvement tourbillonnant

Abrégé

The present invention relates to a rotor (1) for an electric motor of an aircraft, the rotor (1) comprising a shaft (2) made of a first material and a conductor assembly (4) made of a second material that differs from the first material, the rotor (1) being characterized in that the shaft (2) has a shoulder portion (6) having at least one longitudinal slot (25) and in that the conductor assembly (4) is a single-piece structure comprising at least one conducting bar (28) intended to be positioned in the at least one slot (25) and including a skin (29) intended to be fastened onto the shoulder portion.

Classes IPC  ?

• H02K 15/00 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques
• H02K 17/16 - Moteurs asynchrones à induction avec des rotors à enroulement court-circuité à l'intérieur de la machine, p.ex. des rotors à cage
• H02K 17/18 - Moteurs asynchrones à induction avec des rotors à enroulement court-circuité à l'intérieur de la machine, p.ex. des rotors à cage avec des rotors à double cage ou à cages multiples
• H02K 15/02 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques des corps statoriques ou rotoriques
• H02K 1/02 - MACHINES DYNAMO-ÉLECTRIQUES - Détails du circuit magnétique caractérisés par le matériau magnétique

Abrégé

The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue

Abrégé

The present invention relates to a rotor (1) of an aircraft electric motor comprising a shaft (2) made of a first material and a skin (4) made of a second material different from the first material, the rotor (1) being characterized in that the shaft (2) has a shoulder portion (6) to which the skin (4) is attached at the shoulder portion (6), the rotor (1) having an interpenetration layer of the first material and of the second material, the interpenetration layer comprising an alloy of the first material and of the second material.

Classes IPC  ?

• H02K 15/00 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques
• H02K 17/16 - Moteurs asynchrones à induction avec des rotors à enroulement court-circuité à l'intérieur de la machine, p.ex. des rotors à cage
• H02K 15/02 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques des corps statoriques ou rotoriques
• H02K 1/02 - MACHINES DYNAMO-ÉLECTRIQUES - Détails du circuit magnétique caractérisés par le matériau magnétique

Abrégé

The invention relates to a method for training a pilot to cope with a fault affecting one powertrain of a hybrid propulsion system for an aircraft comprising, connected in parallel to a transmission unit, n powertrains (where n≥2), including a first and a second powertrain that are heterogeneous in nature. It involves, during a flight of the aircraft, simulating a fault affecting the first powertrain while, at the same time as performing the simulation, checking the status of the n powertrains of the propulsion system. If a fault affecting one of the n powertrains is detected, the simulation is halted and the instantaneous power delivered by at least one of either the first or the second powertrain is increased so that the sum of the instantaneous powers delivered by the n powertrains is ≥ a minimum total instantaneous power required for the aircraft to continue its flight.

Classes IPC  ?

• G09B 9/44 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité assurant la simulation dans un aéronef réel qui vole à travers l'atmosphère sans limitation de sa trajectoire
• G09B 9/46 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité l'aéronef étant un hélicoptère
• B64C 27/12 - Entraînements des rotors
• G09B 9/08 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité

Abrégé

The invention relates to a sensor (1) for determining a liquid level (NE) for an aircraft tank (100), the determining sensor (1) comprising a closure device (2) for closing a port (101) of the tank (100) and a measuring device (3), removably mounted on the closure device (2), comprising a liquid line (20) configured to convey liquid from the port (100) of the tank (100), and a member (21) for automatically sealing the liquid line (20) if the measuring device (3) is not mounted on the closure device (2), the measuring device (3) comprising at least one pressure measuring member (30) configured to measure a pressure difference between the liquid pressure (P1) in the liquid line (20) and a reference pressure (P2) in order to deduce the liquid level (NE) thereof.

Classes IPC  ?

• G01F 23/16 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p.ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme par mesurage de la pression les dispositifs d'indication, d'enregistrement ou d'alarme étant actionnés par des moyens mécaniques ou hydrauliques, p.ex. en utilisant un gaz, du mercure ou un diaphragme comme élément de transmission, ou par une colonne de liquide
• G01F 22/02 - Procédés ou appareils pour la mesure du volume des fluides ou des matériaux solides fluents, non prévus ailleurs comportant un mesurage de pression
• G01F 23/00 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p.ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme
• F01M 11/12 - Dispositifs indicateurs; Autres dispositifs de sécurité concernant le niveau du lubrifiant

Abrégé

The invention relates to a turboprop (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine (19) having at least a first configuration in which it is mechanically coupled to the propeller shaft (13) and at least one oil pump (21, 21B) configured to supply a hydraulic circuit for adjusting the pitch of the propeller (12). The oil pump is configured to be electrically operated. The invention further relates to an aircraft comprising such a turboprop (10) and to the methods for controlling such a turboprop (10) and such an aircraft.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions

Abrégé

A propeller (2) for an aircraft propulsion assembly (1) extending longitudinally along an axis X, the propeller (2) comprising a propeller cone (21), blades (22), a guide member (4) extending longitudinally along the axis X and rotating as one with the propeller cone (21), the guide member (4) being mounted outside the propeller cone (21) in such a way as to form between them a guide path (V), the guide member (4) having an upstream opening (41) configured to convey a flow of air in the guide path (V) and a downstream opening (42) in such a way as to remove the flow of air downstream, the guide member (4) having through-orifices (40) through which extend the blades (22) of the propeller (2) and compressor vanes (5), which rotate as one with with the propeller cone (21) and which are positioned in the guide path (V) in such a way as to generate an accelerated air flow.

Classes IPC  ?

• B64C 11/14 - Cônes de pénétration
• B64C 11/02 - Construction du moyeu
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion

Abrégé

The invention relates to a device (136) for controlling a power-transfer system (124) for the transfer of power between a high-pressure shaft (108) and a low-pressure shaft (116) of a turbomachine (104) of an aircraft (102), comprising: - a fatigue analysis module (142) analysing the fatigue of the turbomachine (104) and designed to determine, from between two indicators (D1, D2) respectively measuring two fatigues of the turbomachine (104), which is the one that is the most advanced, which is to say which is the one at risk of being first to reach a respective upper limit (D1max, D2max); and - a control module (140) controlling the power transfer system (124) and designed to slow the fatigue measured by the more advanced indicator (D1, D2).

Classes IPC  ?

• 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
• 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 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance
• F02C 3/113 - 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 aves des transmissions de puissance variables entre les rotors

Abrégé

The invention relates to a fire safety system (30) for a turbomachine (1), such as an aeroplane turbofan or a turboprop engine, the turbomachine comprising at least one turbine (3) having a turbine disc (5) and an annular cavity (16) which is arranged upstream of the disc (5), the disc (5) comprising an internal bore (7) and the fire safety system (30) comprising a cooling device (14) intended to supply the cavity (16) with cooling air via injection means (17). According to the invention, the fire safety system (30) comprises means configured such that, on the one hand, the annular cavity is divided into a first cavity and a second cavity and, on the other hand, a cooling air speed is maintained at the outlet of the injection means (16) and the cooling air in the first cavity is guided to the internal bore (7) of the turbine disc (5). Said means comprise a diffuser (52) co-operating with the injection means (17) and an annular cover intended to co-operate with the diffuser (52) and to cover first attachment members (27) arranged in the cavity (16), the diffuser (52) and the cover (40) being configured such that the cooling air at the outlet of the diffuser (52) is at least partially guided by a radially outer surface (40a) of the cover (40).

Classes IPC  ?

• F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
• 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
• F01D 25/12 - Refroidissement
• F01D 25/18 - Systèmes de lubrification
• F02C 7/25 - Prévention ou protection contre l'incendie

Abrégé

The invention relates to a system (100) which comprises: a gas turbine (102) designed so that a combustion chamber (110) can be ignited in a first ignition range of rotational speeds of a compressor shaft (112); and a control device (106) designed to control an electric starter (114) to accelerate the compressor shaft (112), and, when the compressor shaft (112) is accelerated, to control an attempt to ignite the combustion chamber (110). The gas turbine (102) is designed so that the combustion chamber (110) can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.

Classes IPC  ?

• F02C 7/26 - Démarrage; Allumage
• F02C 7/262 - Redémarrage après extinction
• F02C 7/268 - Entraînement du rotor pour le démarrage

Abrégé

A rotor wheel (10) for an aircraft turbine engine, said wheel comprising: - a disc (12) having a main axis (A) and provided with cells (14) at its outer periphery, the cells extending along the axis and each comprising a bottom (14a) and two side flanks (14b), - vanes (22) mounted in the cells (14) of the disc (12), each of said vanes comprising a blade (24) connected by a platform (26) to a root (28) which is configured to be interlockingly mounted in one of the cells (14), the root (28) of each of the vanes (22) comprising, at its radially inner end, a lobe (30) with a first axial end which comprises a circumferential notch (32) and a second axial end, opposite the first end, which comprises a radially inward facing stop (33) configured to axially bear on a first face (12b) of the disc (12), and - a split annular ring (34) engaged in the notches (32) of the vanes (22) and axially clamped against a second face (12a) of the disc, the second face (12a) being opposite the first face (12b), the lobe (30) of the root (28) of each of the vanes (22) comprising, between the first and second ends, a radially inward facing projecting bulb (42) configured to radially bear on the surface of the bottom (14a) of the corresponding cell (14).

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales
• F01D 5/32 - Verrouillage, p.ex. par des aubes terminales de verrouillage ou par des clavettes
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages

Abrégé

The invention relates to a turbomachine comprising a rotary body comprising a motor shaft supplying mechanical power, and at least one magnetic drive pump comprising at least: one stator (110) delimiting an annular inner space and comprising a first and a second flange (1110, 1120), a rotor (120) arranged in the inner space between the first and second flanges and capable of driving fluid, the rotor being able to rotate about an axis of rotation (A), a pair of magnets (1241, 1242) having opposite polarities coaxially arranged on the rotor with the axis of rotation, a magnet (1116) arranged on the first flange (1110) in order to co-operate with one of the magnets of the pair of magnets of the rotor, a magnetic means (130) for rotating the rotor arranged on the second flange (1120), the second flange being non-magnetic.

Classes IPC  ?

• F02C 7/22 - Systèmes d'alimentation en combustible
• F04D 29/048 - Paliers électromagnétiques

Abrégé

A device (110) for guiding a main air flow (F1) for an aircraft turbine engine (22), said device comprising: a first air flowing pipe (112) of a main air flow (F1), said first pipe having a main axis (A), - a plurality of ejectors (114) of a secondary air flow (F2) located within the first pipe (112) and configured to eject a secondary air flow (F2) and force the flow of the main air flow (F1) into said first pipe (112), the ejectors (114) being distributed around the main axis (A), and - a second air flowing pipe (116) located at the outlet of the ejectors (114) and comprising one end (116a) which is connected to one end (112a) of the first pipe (112), characterised in that the second pipe (116) comprises a narrow end (134).

Classes IPC  ?

• F02C 7/052 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des dispositifs séparateurs de poussière
• F04F 5/16 - Pompes à jet, p.ex. dispositifs dans lesquels le flux est produit par la chute de pression causée par la vitesse d'un autre fluide le fluide inducteur étant un fluide compressible déplaçant des fluides compressibles
• F04F 5/46 - Aménagements des tuyères

Abrégé

The invention relates to a transmission device (1) for hybrid aircraft comprising a turboshaft engine having a gas generator (12), a free turbine (14), and a main rotor (52), the device comprising a first reversible electric motor (30) coupled to a shaft (16) of the free turbine (14) via a first disengageable coupling means (32), and to the main rotor (52), and a second reversible electric motor (40) coupled to a shaft (18) of the gas generator (12) via a second disengageable coupling means (44), and coupled to the main rotor (52) via a third disengageable coupling means (42), the second disengageable coupling means (44) being operable when the second electric motor (40) rotates in a first direction of rotation, and the third disengageable coupling means (42) being operable when the second electric motor (40) rotates in a second direction of rotation opposite to the first direction of rotation.

Classes IPC  ?

• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B60K 6/50 - Architecture de la chaîne cinématique caractérisée par l'agencement ou la nature des ensembles de transmission
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• B64D 35/02 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le type de groupe moteur
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs

Abrégé

The system comprises: - a fuel tank; - a suction pipe that is connected to the tank and is located higher than the tank; - an electric pump (36); - a supply pump configured to be mechanically driven by an accessory gear box and be connected, at the outlet, to a fuel supply circuit for the engine; and - an air evacuation drain (26). The electric pump (36) is in communication with the suction pipe independently of the supply pump, and with the drain. The supply pump is in communication with the suction pipe independently of the electric pump.

Classes IPC  ?

• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

Classes IPC  ?

• H02P 29/10 - Prévention de la survitesse ou la sous-vitesse

Abrégé

The invention relates to a turbomachine comprising a gas generator (13) equipped with a first shaft (18), an accessories box (14), at least one reversible electrical machine (11) coupled with the accessories box (14), a free turbine (12) equipped with a second shaft (17) and driven in rotation by a gas flow from the gas generator (13), and at least one accessory (15, 16) coupled to the accessories box (14). The turbomachine (10) comprises a first mechanical coupling means (20) configured to mechanically couple the first mechanical shaft (18) to the accessories box (14) in a first configuration and to mechanically uncouple said first mechanical shaft (18) from the accessories box (14) in a second configuration, and a second mechanical coupling means (25) configured to mechanically couple the second mechanical shaft (17) to the accessories box (14) in a first configuration and to mechanically uncouple said second mechanical shaft (17) from the accessories box (14) in a second configuration, the electrical machine (11) being sized to drive the gas generator and the at least one accessory when the turbomachine is started.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

A fixed-wing combat aircraft (10) comprising an electrical power source (20), a propulsion system (30), a low-power non-propulsion assembly (40) comprising a flight control system, a high-power non-propulsion assembly (50) comprising an electrical weapon system (52), and a management unit (60) configured to selectively establish on command multiple operating modes comprising: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.

Classes IPC  ?

• B64D 7/00 - Agencement à bord aéronefs des équipements militaires, p.ex. des armes, des accessoires d'armement ou des blindages de protection; Adaptations des installations d'armement aux aéronefs
• F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs

Abrégé

The invention relates to a system (400) for pumping and metering a fluid (10) for a turbine engine, which system comprises at least one pump (412, 414) for the fluid and an electronic computer (430) configured to determine the flow rate of the fluid to be delivered to the turbine engine, the pumping and metering system being characterised in that it further comprises a first electric motor and a second electric motor, which are each configured to drive the at least one pump, and in that the electronic computer comprises a first control loop (432) for controlling at least the first electric motor and a second control loop (434) for controlling at least the second electric motor.

Classes IPC  ?

• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 9/46 - Commande de secours de l'alimentation en combustible
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels

Abrégé

A turbine (1) for a turbomachine of longitudinal axis (X), comprising: an alternating arrangement of annular rows of movable blades (64) and of fixed blades (65) and a radially inner annular cavity (68) formed radially inside the movable and fixed blades (64, 65), and a supply circuit (32) for supplying cooling air to the inner annular cavity (68), the downstream end of the supply circuit (32) comprising an inner annular row of orifices (81) and an outer annular row of orifices (82) opening into the radially inner annular cavity (68), the turbine further comprising means (85) for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices (81, 82).

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
• F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
• F01D 25/12 - Refroidissement

Abrégé

Disclosed is a rotor (121) for a centrifugal breather for an air/oil mixture of a turbomachine, this rotor comprising: a hollow shaft (114) extending along an axis (X), a pinion (115) for rotating the hollow shaft (114), this pinion (115) extending around the axis (X) and being formed of a single part and in a first material with at least one first portion (114a) of the hollow shaft (114), and an annular structure (117) extending around the axis (X) and constrained to rotate with the shaft (114), this structure (117) being produced in a second material, different from the first material, characterised in that said structure (117) is made integral with the shaft (114) by additive manufacturing of this structure directly on at least one annular surface (122) of the pinion (115) which forms at least one annular support surface for this additive manufacturing.

Classes IPC  ?

• F01M 11/08 - Séparation du lubrifiant de l'air ou du mélange air-carburant avant introduction dans le cylindre
• B01D 39/20 - Autres substances filtrantes autoportantes en substance inorganique, p.ex. papier d'amiante ou substance filtrante métallique faite de fils métalliques non-tissés
• B01D 45/14 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par des pales, disques, tambours ou brosses rotatives
• B04B 5/08 - Centrifugeurs pour séparer des mélanges essentiellement gazeux
• B04B 7/08 - Tambours rotatifs
• F01D 25/18 - Systèmes de lubrification
• F01M 13/04 - Ventilation ou aération du carter par des moyens épurant l'air avant qu'il ne sorte du carter, p.ex. des séparateurs d'huile

Abrégé

Ignition method for a continuous combustion engine comprising an electronic engine control member (7), a high-power housing (2), a spark plug ignition circuit and a solenoid fuel valve engaging with a starter, the method being implemented by the electronic engine control member (7) and comprising a pre-charging step (03) of pre-charging the high-power housing (2) prior to an engine-starting step (E3) initiated upon an instruction to start the engine (02), the pre-charging step (03) being controlled: - by switching on the electronic engine control member (7), - or by putting the engine in idle mode (OV).

Classes IPC  ?

• F02C 7/26 - Démarrage; Allumage
• F02C 7/262 - Redémarrage après extinction
• F02C 7/266 - Allumage électrique

Abrégé

A double wall (2) for an aircraft gas turbine combustion chamber (1) comprising an internal wall (21) which is configured to be in contact with the combustion reaction, and an external wall (22) which is at a distance from the internal wall (21), comprising a plurality of openings (3) so as to allow the circulation of cooling air streams (F), outside the external wall (22), which cool the internal wall (21), the internal wall (21) being free of perforations so as to prevent any circulation of a cooling air stream (F) towards the centre of the combustion chamber (1). The double wall (2) is characterised in that the internal wall (21) comprises a plurality of members (4) projecting towards the external wall (22), each projecting member (4) comprising a foot portion (4a) and a cylindrical head portion (4b) with a circular cross-section, the head portion (4b) extending into an opening (3) with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member (4) and the opening (3), through which area a cooling air stream (F) can flow.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Abrégé

The invention relates to an assembly (1) for transmitting and measuring a torque transmitted between a first member and a second member (16) of a turbomachine, comprising a pinion (2) which includes a first annular portion (5) and a second annular portion (6) joining together at a connecting portion (7) supporting a gear system (4) of the pinion (2), the first and second annular portions (5, 6) extending axially along an axis of rotation (X) of the pinion (2) in directions (D1, D2) opposite from the connecting portion (7), the rotation of at least one of the the annular portions (5, 6) being guided via a bearing (8, 9) for guiding the pinion (2), the pinion further comprising an axially extending power shaft (10), the power shaft (10) comprising a first area (11) rotatably coupled to the first annular portion (5) of the pinion (2), and a second area (12) intended to be rotatably coupled to the second member (16) of the turbomachine, the first area being axially spaced apart from the second area, and means for measuring the torsion of the power shaft (10) which are arranged in a third area of the power shaft (10) located between the first and second areas (11, 12), the measuring means comprising at least one tone wheel (20, 25) and acquisition means capable of engaging with the tone wheel (20, 25), characterised in that the measuring means comprise a first tone wheel (20) provided in the third area of the power shaft (10) and a second tone wheel (25) provided in the second annular portion (6) of the pinion (2) and located axially opposite the first tone wheel (20), the acquisition means being arranged axially opposite the first tone wheel (20) and the second tone wheel (25) and being configured to supply a signal representative of an angular variation between the first tone wheel (20) and the second tone wheel (25).

Classes IPC  ?

• G01L 3/10 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple comporte un arbre élastique en torsion impliquant des moyens électriques ou magnétiques d'indication

Abrégé

Disclosed is a propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) comprising an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). The assistance device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to function as an electric generator in order to take off energy produced by the main engine (9), and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine being supplied with electricity by the first electric machine and configured to function as an electric motor in order to deliver additional mechanical power to the main gearbox (4).

Classes IPC  ?

• B64C 27/04 - Hélicoptères
• B64C 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 35/02 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le type de groupe moteur

Abrégé

ref1ref223211) and, - controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• 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

Abrégé

The invention relates to a method for determining at least one minimum power margin of a hybrid drive train for a transport vehicle, each drive element being associated with at least one power source and at least one power consumer, the method comprising a step of acquiring (ET1) measurements (Pv) of power parameters (PARi), a step of comparing (ET2) each measurement (Pv) with at least one limitation threshold, so as to deduce therefrom at least one gross margin (Pmb), a step of converting (ET3) the gross margins (Pmb) into refined margins (Pma) expressed according to the same common magnitude, a step of transposing (ET4) into standardised margins (Pmn) at least at one reference point, a step of determining (ET5) a source power margin (MIndS) and a consumer power margin (MIndC) at said reference point and a step of determining (ET6) the minimum power margin (MInd) by selecting the lowest power margin.

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 43/00 - Aménagements ou adaptations des instruments
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs

Abrégé

Device (30) for controlling an airflow guiding system (20), comprising at least one actuator (31) configured to translate a control rod (32) between a first and a second end position of a nominal operating range in which at least one vane (21a) of the airflow guiding system (20) can be moved between a first and a second angle, the control rod (32) being connected to the vane (21a) by a control lever (33) comprising a first control rod (36) and a second control rod (37) which are hinged together. The actuator (31) is configured to bring the control rod (32) into a safety position located beyond the second end position of the nominal operating range and to orient the vane (21a) at a safe pitch angle between the first angle and the second angle.

Classes IPC  ?

• F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
• F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables

Abrégé

The invention relates to a turbomachine (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), a rotating electric machine (19), having at least a first configuration in which it is mechanically coupled to the propeller shaft (13), and a motor oil pump (21) supplying a lubricating circuit (20) of the turbomachine (10). The rotating electric machine (19) in the first configuration is mechanically coupled to the motor oil pump (21) in such a way that the rotating electric machine (19) additionally drives the motor oil pump (21) when it is supplied with current. The invention further relates to an aircraft comprising such a turbomachine (10).

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/06 - Aménagement des paliers; Lubrification
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

A turbomachine (10), in particular for a rotary-wing aircraft, having a gas generator (13) provided with a rotary shaft (18), a reversible first electric machine (11), a free turbine (12) driven in rotation by a flow of gas generated by the gas generator (13), at least one accessory (15, 16) selected from an oil pump and a fuel pump, an accessories gearbox (14) comprising a gear train configured to drive said at least one accessory (15, 16), and a second electric machine (19). The second electric machine (19) is reversible, said first electric machine (11) is mechanically coupled to the gas generator (13), the accessories gearbox (14) and the second electric machine (19) are mechanically coupled to the free turbine (12), and the turbomachine (10) does not have a kinematic link between the gear train of the accessories gearbox (14) and the shaft (18) of the gas generator (13).

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique

Abrégé

The invention relates to a method for determining an efficiency fault (R11-R15) of at least one module (11-15) of a turboshaft engine (T) of an aircraft (A), the method for determining comprising: • A step of determining an estimated real mapping (CARE), • A step of determining real indicators (IRE) from the estimated real mapping (CARE), • A step of determining (E3) a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine (T) for different efficiency configurations, • A step of determining (E4) simulated indicators (ISx) for each simulated mapping (CARSx), • A step of training (E5) a mathematical model (CLASS) by coupling the simulated indicators (ISx) with efficiency configurations (CR), and • A step of applying (E6) said mathematical model (CLASS) to the real indicators (IRE) so as to deduce therefrom a real efficiency configuration (CR).

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
• G05B 23/02 - Test ou contrôle électrique

Abrégé

Disclosed is a turbomachine comprising a gas generator (13) provided with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• 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
• F02C 7/26 - Démarrage; Allumage
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

Disclosed is a turbogenerator (10), in particular for an electrically-driven rotary wing aircraft, comprising a gas generator (13) provided with a first shaft (18), at least one reversible electrical machine (11), and a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13). The second shaft (17) is coupled to the at least one electrical machine (11) during all phases of operation of the turbogenerator (10), and the turbogenerator (10) further comprises a single mechanical coupling means (20) for coupling said first mechanical shaft (18) to said second mechanical shaft (17) when the electrical machine (11) is operating in motor mode and mechanically uncoupling said first mechanical shaft (18) from said second mechanical shaft (17) when the electrical machine (11) is operating in generator mode.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• 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
• F02C 7/26 - Démarrage; Allumage
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique

Abrégé

Hybrid turbomachine (1) comprising an electrical generator (2), a gas generator (3) provided with an air intake (31) and an exhaust (32) and an acoustic control system (4) comprising a control unit (41) and a plurality of loudspeakers. At least a first loudspeaker (43) is arranged on the electrical generator (2) and/or at least a second loudspeaker (45) is arranged at the air intake (31) of the gas generator (3) and/or at least a third loudspeaker (47) is arranged at the exhaust (32) of the gas generator (3). The control unit (41) of the acoustic control system (4) is mounted on the electrical generator (2) and is configured to perform an AC/DC electrical conversion of the electromotive force of the electrical generator (2) into an adjustable direct-current voltage which is intended to be distributed to loads or to energy storage means.

Classes IPC  ?

• F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

Disclosed is a method for protecting windings from excessive heating in an aircraft electrical machine comprising a stator (12) and a rotor (14) configured to be driven in rotation with respect to one another, the stator comprising a plurality of notches (120) receiving the same or different plurality of windings, the method comprising the following successive steps: inserting an electrical insulator (16) into the notches or on the teeth of the stator, positioning the windings (18) in the notches or on the teeth of the stator, casting a phase-change material (20) into the notches or onto the teeth provided with the windings, the electrical insulator forming a casting mould.

Classes IPC  ?

• H02K 15/10 - Application d'un isolant sous forme solide à des enroulements, des stators ou des rotors
• H02K 3/34 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement entre conducteurs ou entre conducteur et noyau, p.ex. isolement d'encoches
• C09K 5/06 - Substances qui subissent un changement d'état physique lors de leur utilisation le changement d'état se faisant par passage de l'état liquide à l'état solide, ou vice versa
• H02K 9/20 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile dans lesquels l'agent de refroidissement se vaporise dans l'enveloppe de la machine

Abrégé

An aspect of the invention relates to a start-up method (100) for an aircraft engine (1), wherein the engine (1) is connected to a lubrication circuit (6) comprising, in particular, an oil pump system (7), the lubrication circuit (6) being constructed and arranged to circulate oil in the engine (1), and wherein an operating mode of the engine (1) comprises a stop mode and a standby mode, the start-up method (100) being characterised in that it comprises, during a start-up phase, the steps of: - measuring (101) an oil temperature, the measuring step (101) being carried out by a temperature detection device; - as a function of the temperature measured compared with a threshold temperature, and as a function of the operating mode of the engine, selecting (102) an oil flow profile for start-up to be applied in the engine, the step of selecting (102) being carried out by a computer; - applying (103) the oil flow profile for start-up selected by means of the oil pump system, the oil pump system being controlled by the computer.

Classes IPC  ?

• F01D 25/10 - Chauffage, p.ex. réchauffage avant démarrage
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

The invention relates to a circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules comprising an annular peripheral module (3) and a circular central module (2).

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
• B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 10/37 - Commande ou régulation des opérations des caractéristiques du lit de poudre, p.ex. de la densité
• B22F 10/47 - Structures destinées à soutenir des pièces ou des articles pendant la fabrication et retirées par la suite caractérisées par des caractéristiques structurelles
• B22F 10/60 - Traitement de pièces ou d'articles après leur formation
• B29C 64/245 - Plates-formes ou substrats
• B29C 64/30 - Opérations ou équipements auxiliaires
• B29C 64/379 - Manutention des objets en 3D obtenus, p.ex. à l’aide de robots
• B29C 64/40 - Structures de support des objets en 3D pendant la fabrication, lesdites structures devant être sacrifiées après réalisation de la fabrication
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
• B33Y 40/20 - Posttraitement, p.ex. durcissement, revêtement ou polissage

Abrégé

The invention relates to a propulsion unit (22) with a propeller (26), comprising: - a nacelle (24); - a propeller (26) rotatably mounted in the nacelle (24) by means of a hub (28), the propeller (26) comprising blades (32) mounted in a blade cuff (38) pivotable about a pitch axis (Y) relative to the hub (28), each blade (32) being pivotable relative to the cuff (38) about a folding axis (Z); - a folding device (50) that comprises an actuator (52) for folding the blades (32); the propulsion unit (22) being characterised in that the folding device (50) comprises a control member (56) rotationally affixed to the blade cuff (38) and driven by the actuator (52), and a connecting rod (58) pivotably mounted, on the one hand, on a root (34) of the associated blade (32) and, on the other hand, on the movable control member (56).

Classes IPC  ?

• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/28 - Pales rabattables ou repliables

Abrégé

Aircraft turbomachine (10), comprising: a centrifugal compressor (14), a combustion chamber (24), the combustion chamber being supplied by the compressor via a diffuser (34) and via a straightener (36), and a heat exchanger (38), the exchanger comprising: a first circuit (38a), supplied with exhaust gas from the turbomachine, and a second circuit (38b), which are connected by volutes (40a, 40b) on the one hand to an outlet (34b) of the diffuser (34) and on the other hand to an inlet (36a) of the straightener (36), the volutes (40a, 40b) having reversed winding directions such that their connection ports to the exchanger (38) are independent of one another and are substantially diametrically opposed, and such that the minimum cross section (S2) of each duct is situated at a larger cross section of the other duct.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement
• F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
• F04D 29/42 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges

Abrégé

The invention proposes that bridges (9) extending adjacent to each other integrally link a radially inner wall (5) and a radially outer wall (3) of a combustion chamber of a gas turbine engine towards a free end (5a) of the radially inner wall (5), the whole being an additive layer structure.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Abrégé

The invention relates to a propulsion unit (22) having a propeller (26) for an aircraft (20), comprising: - a nacelle (24); - a propeller (26) mounted in the nacelle (24) so as to be capable of rotating about a longitudinal axis (X) of rotation, the propeller (26) having blades (32) mounted by a root (34) so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis (X) of rotation, and a folded position, in which they are longitudinally received against the nacelle (24); - drive means that rotate the propeller (26); indexing means for stopping the propeller (26) in at least one indexed angular position (θ i) relative to the nacelle (24); the propulsion unit (22) being characterised in that the indexing means consist of a stepping electric motor (82) comprising a rotor (84) that is coupled to the propeller (26).

Classes IPC  ?

• B64C 11/28 - Pales rabattables ou repliables

Abrégé

This electromechanical installation (100) for an aircraft comprises: - an electrical network (102) comprising electrical subnetworks (104, 106); - a turbogenerator (118) comprising a gas turbine (120), an electricity generator (122) with permanent magnets having phase groups (126, 128) respectively connected to the electrical subnetworks (104, 106), and, for each phase group (126, 128), an isolation device (134, 136); and - a control device (140) designed to detect a short circuit in at least one of the phase groups, each phase group in which a short circuit is detected being described as defective and each other phase group being described as healthy, and, in response to the detection of the short circuit, to disconnect this defective phase group (126, 128) from its associated electrical subnetwork (104, 106) and to command the shutdown of the gas turbine (120). The control device (140) is also designed, in response to the detection of the short circuit, to keep each healthy phase group (126, 128) connected to its electrical subnetwork (104, 106).

Classes IPC  ?

• H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• H02H 7/06 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour compensateurs synchrones
• H02P 3/00 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• 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

Abrégé

The invention relates to a propulsion unit (22) with a propeller (26), comprising: - a nacelle (24); - a propeller (26) rotatably mounted in the nacelle (24) by means of a hub (28), the propeller (26) comprising blades (32) mounted in a blade cuff (38) pivotable about a pitch axis (Y) relative to the hub (28), each blade (32) being pivotable relative to the cuff (38) about a folding axis (Z); - a folding device (50) that comprises an actuator (52) for folding the blades (32); the propulsion unit being characterised in that the folding device (50) comprises a control member (56) rotationally affixed to the blade cuff (38) and driven by the actuator (52), and a connecting rod (58) pivotably mounted, on the one hand, on a root (34) of the associated blade (32) and, on the other hand, on the movable control member (56).

Classes IPC  ?

• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/28 - Pales rabattables ou repliables

Abrégé

Aircraft turbomachine (11), comprising: - a centrifugal compressor (12), - an annular combustion chamber (24), - an annular casing (29) extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and - a heat exchanger (38), this exchanger comprising a first circuit (38a) supplied with exhaust gas from the turbomachine, and a second circuit (38b) connected by volutes (40a, 40b) respectively to an outlet (34b) of the compressor (12) and to said space (E), characterized in that the volutes (40a, 40b) are at an axial distance from one another, and in that the second volute (40b) is connected to the space (E) by a straightener (42) which is situated at least in part outside the casing (29) and which is integrated into an annular connecting pipe (44) which connects the second volute (40b) to this casing (29).

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F01D 9/02 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage
• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement
• F04D 29/42 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges

Abrégé

The invention relates to a hydraulic torque measurement device for an aircraft engine unit, comprising: a hermetically sealed enclosure (20a) comprising a rigid wall (21) and a deformable wall (22) defining an internal volume (26), and at least one pressure measuring element (28) capable of measuring the pressure prevailing in the internal volume (26), the hydraulic device (20) allowing a service state in which the internal volume (26) is filled exclusively with an incompressible liquid, and in which the deformable wall (22) is configured to be subjected to a pressure force. The invention further relates to a gearbox comprising such a hydraulic device.

Classes IPC  ?

• G01L 5/12 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de la poussée axiale d'un arbre tournant, p.ex. matériel de propulsion
• G01L 3/14 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple est autre qu'un arbre élastique en torsion

Abrégé

The invention relates to a turbomachine having a compressor comprising variable pitch stator vanes (11) each extending radially between a rotating hub (6) and a stationary casing (3) surrounding this rotating hub (6), each variable pitch vane (11) comprising a blade (12) having a base (14) spaced by a first radial clearance (J1) from a stationary wall (2) of the casing (3), and a tip (17) spaced by a second radial clearance (J2) from a rotating wall (4) of the rotating hub (6). The stationary wall of the casing (3) or the rotating wall (4) of the rotating hub (6) has a shape treatment opposite the blade (12) for channeling an air leak passing through the corresponding clearance.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
• F04D 29/52 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes axiales
• F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analogues; Equilibrage en agissant sur les couches limites

Abrégé

The invention relates to an oro-nasal respiratory mask (1) comprising an airtight body (2) comprising an edge (3) intended to be sealably applied onto the face of a user, the body (2) comprising at least one opening (4) allowing the passage of an inhalation air flow and an exhalation air flow, a filter (5) being detachably and sealably mounted in the opening (4) of the body (2) so that the inhalation and exhalation air flows fully pass through said filter (5).

Classes IPC  ?

• A41D 13/11 - Masques de protection du visage, p.ex. pour utilisation chirurgicale ou pour utilisation en atmosphère polluée

Abrégé

The invention relates to a modular tray (12) for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it comprises: - a circular shaft module (13) comprising a shaft provided with a circular tray at one end thereof, the shaft and the circular tray being concentric; and - a main support module (16) having a cavity (17) in one face configured to receive the circular shaft module (13), the shaft being inserted completely into the cavity; the assembly of the circular shaft module and the main support module defining a planar upper surface which is formed at least in part by the circular tray of the circular shaft module. A modular tray (12) for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it comprises: a circular shaft module (13) comprising a shaft provided with a circular tray at one end thereof, the shaft and the circular tray being concentric; and a main support module (16) having a cavity (17) in one face configured to receive the circular shaft module (13), the shaft being inserted completely into the cavity; the assembly of the circular shaft module and the main support module defining a planar upper surface which is formed at least in part by the circular tray of the circular shaft module.

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
• B29C 64/245 - Plates-formes ou substrats
• B29C 64/40 - Structures de support des objets en 3D pendant la fabrication, lesdites structures devant être sacrifiées après réalisation de la fabrication
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
• B33Y 80/00 - Produits obtenus par fabrication additive
• B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma

Abrégé

Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
• B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines

Abrégé

The invention relates to a combustion assembly for a gas turbine, comprising a flame tube (14) and fuel supply means having a flow limiter (18) which supplies an injector (19), the flow limiter (18) and the fuel injector (19) being formed in a single piece.

Classes IPC  ?

• F02C 7/22 - Systèmes d'alimentation en combustible
• F23D 11/38 - Ajutages; Dispositifs de nettoyage des ajutages
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F02C 9/26 - Commande de l'alimentation en combustible

Abrégé

The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially inner end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 5/20 - Extrémités de pales spécialement façonnées en vue d'obturer l'espace entre ces extrémités et le stator
• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analogues; Equilibrage en agissant sur les couches limites

Abrégé

The invention relates to a fuel supply circuit of an aircraft engine, comprising a centrifugal pump which is mechanically coupled to a drive shaft (18) delivering a mechanical power. The circuit further comprises at least one electromagnetic pump (100) having at least one stator (110) which delimits an annular internal volume, in which a rotor (120) capable of driving a fluid is present, a plurality of magnets (130) which are distributed annularly around the rotor (120), and at least a plurality of coils (140) which are distributed annularly inside the stator (110) opposite the magnets (130). The rotor (120) is connected to the drive shaft (18) by means of a unidirectional clutch element (150).

Classes IPC  ?

• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F02C 7/26 - Démarrage; Allumage
• F02C 9/30 - Commande de l'alimentation en combustible caractérisée par un débit variable d'une pompe à combustible
• F02C 7/22 - Systèmes d'alimentation en combustible
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

Disclosed is a method for manufacturing a vane (10) comprising a first portion and a second portion, the method comprising a step of forming the first portion (E1) that comprises forming a model of the first portion from removable material, then forming a first shell mould from the model of the first portion, then forming the single-crystal or columnar first portion from a first metal alloy in the first shell mould from a single-crystal seed, a step of forming the second portion (E2) in which a second portion is formed on the first portion, and in which the first portion and the second portion are made from different materials, the second portion being polycrystalline and formed from a second metal alloy. Also disclosed is a vane (10) comprising a single-crystal or columnar first portion made from a first metal alloy and a polycrystalline second portion made from a second metal alloy different from the first metal alloy.

Classes IPC  ?

• B22C 9/04 - Emploi des modèles perdus
• B22C 9/22 - Moules pour pièces de forme particulière
• B22C 9/24 - Moules pour pièces de forme particulière pour pièces évidées
• B22D 19/04 - Coulée dans, sur, ou autour d'objets formant partie intégrante du produit final pour raccorder des pièces
• B22D 19/16 - Coulée dans, sur, ou autour d'objets formant partie intégrante du produit final pour fabriquer des moulages composites à partir de métaux différents, p.ex. pour fabriquer des cylindres de laminoirs
• B22D 21/02 - Coulée de métaux non ferreux très oxydables, p.ex. atmosphère inerte
• B22D 27/04 - Action sur la température du métal, p.ex. par chauffage ou refroidissement du moule
• C30B 29/52 - Alliages
• C30B 11/00 - Croissance des monocristaux par simple solidification ou dans un gradient de température, p.ex. méthode de Bridgman-Stockbarger
• C30B 29/60 - Monocristaux ou matériaux polycristallins homogènes de structure déterminée caractérisés par leurs matériaux ou par leur forme caractérisés par la forme
• C30B 29/66 - Cristaux de forme géométrique complexe, p.ex. tubes, cylindres

Abrégé

Three-point contact rolling bearing (1) wherein the internal raceway (12), the third contact point (P3) being situated in a sector of the external raceway (22) delimited by a proximal end of the external raceway (22) on one side, and by the rolling plane (Pr) on the other side, characterized in that the external ring (20) comprises a drain (50) that is provided in the external raceway (22) and opens out at an external surface of the external ring (20), said drain (50) opening onto the external raceway (22) in an off-centre manner with respect to the rolling plane (Pr), in a sector of the external raceway (22) that is delimited by the rolling plane (Pr) on one side, and by a distal end of the external raceway (22) on the other side, the drain (50) and the third contact point (P3) being separated from one another.

Classes IPC  ?

• F16C 19/16 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec roulements à billes essentiellement du même calibre, en une ou plusieurs rangées circulaires pour charges à la fois radiales et axiales avec une seule rangée de billes
• F16C 33/66 - Pièces ou détails particuliers pour la lubrification

Abrégé

Turbogenerator (1) for an aircraft (2) comprising: - a turboshaft engine (3); - an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric generator (4); characterized in that the turbogenerator (1) comprises a static separator (8) for separating an air/oil mixture coming from the turboshaft engine (3), the static separator (8) being positioned around the housing (7) of the electric generator (4).

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliers; Lubrification
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• B01D 45/08 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge par inertie par projection contre les diaphragmes séparateurs

Abrégé

System (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, comprising at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
• B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• H02P 5/68 - Dispositions spécialement adaptées à la régulation ou la commande de la vitesse ou du couple d’au moins deux moteurs électriques pour commander au moins deux moteurs dynamo-électriques à courant continu

Abrégé

The document relates to a device for supplying fuel to a combustion chamber of a gas generator, comprising: - a wheel (14) for injecting fuel into the combustion chamber (18), - a fuel supply rail (20) comprising an internal fuel circuit (30) which comprises fuel outlet means (32) supplying fuel to an annular spray chamber (24) formed between the ramp (28, 44, 48, 52, 56) and the injection wheel (14), - at least one dynamic annular seal (26) designed to provide a seal between an annular face (34) of the fuel supply rail (28, 44, 48, 52, 56) and the injection wheel (14), characterised in that the fuel circuit (30) of the fuel supply rail comprises an annular fuel flow portion arranged radially in the dynamic annular seal (26).

Classes IPC  ?

• F02C 3/16 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail caractérisés par l'aménagement de la chambre de combustion dans l'ensemble les chambres de combustion étant formées au moins partiellement dans le rotor de la turbine
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• F23R 3/38 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible comprenant des moyens d'injection de combustible rotatifs

Abrégé

AA).

Classes IPC  ?

• F04C 2/10 - Machines ou pompes à piston rotatif du type à engrènement extérieur, c. à d. avec un engagement des organes coopérants semblable à celui d'engrenages dentés du type à axe interne, l'organe externe ayant plus de dents ou de parties équivalentes de prise, p.ex. de rouleaux, que l'organe interne
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F04C 7/00 - "Machines" ou pompes à piston rotatif avec anneau fluide ou dispositif analogue
• F04C 15/00 - "MACHINES" À LIQUIDES À DÉPLACEMENT POSITIF, À PISTON ROTATIF OU OSCILLANT; POMPES À DÉPLACEMENT POSITIF, À PISTON ROTATIF OU OSCILLANT - Parties constitutives, détails ou accessoires des "machines", des pompes ou installations de pompage non couverts par les groupes

Abrégé

The invention relates to a cold expansion device (36) for work hardening a through bore (34) in a turbine engine part (32), comprising at least one chuck (38) supporting a burnisher (40) and a means (41) for pushing the chuck (38) in an axial direction, and is characterised in that it comprises at least: - a tubular guide (42) configured to guide the burnisher (40) to the bore (34), - a first magnetic attachment means (51) arranged at a free end (44) of the chuck (38), - the burnisher (40), comprising a work surface (46) and an end (48) comprising second magnetic attachment means (49) complementary to the first magnetic attachment means (51), and in that the axial pushing means (41) is configured to push the burnisher through the bore (34) until it emerges from said bore.

Classes IPC  ?

• B24B 39/02 - Machines ou dispositifs à brunir, c. à d. utilisant des organes de pression pour durcir les surfaces; Accessoires à cet effet pour travailler intérieurement des surfaces de révolution

Abrégé

The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) includes a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the wall (20b) has piston actuator mechanisms (23, 23'), each actuator mechanism being actuatable independently of the others and being designed to cooperate with means (24, 24') built into an inner surface (20b') of the wall (20b) so as to deform the wall (20b) in a radial direction in relation to said axis (X) under the effect of a predetermined displacement command.

Classes IPC  ?

• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
• B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
• F02K 1/10 - Variation de la section utile de la tubulure de jet ou de la tuyère par déviation de la tubulure de jet ou de la tuyère

Abrégé

The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23') extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.

Classes IPC  ?

• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
• B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
• F02K 1/10 - Variation de la section utile de la tubulure de jet ou de la tuyère par déviation de la tubulure de jet ou de la tuyère

Abrégé

Disclosed is a method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request (100) by a pilot of the helicopter to quickly stop the engine, the following steps managed by the control unit of the turbomachine: - detecting (110) the absence of a thermal stabilisation phase of the gas generator of at least one turbomachine, - controlling (130) the extinguishing of the combustion chamber of the gas generator of at least one turbomachine, - maintaining the rotation of the gas generator (140) whose combustion chamber has been extinguished by means of the at least one electrical machine in order to ventilate the gas generator, and - stopping (160) the main rotor of the helicopter by means of a mechanical brake.

Classes IPC  ?

• F01D 21/12 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à la température
• F02C 9/46 - Commande de secours de l'alimentation en combustible
• F02C 7/25 - Prévention ou protection contre l'incendie

Abrégé

The invention relates to a propulsion system (1, 1') for an aircraft, in particular a vertical take-off and landing (VTOL) aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), at least one part of one of said walls being made of a deformable shape memory material, said wall being provided with heating elements (23a, 23c) extending in different consecutive angular sectors about said axis (X), each heating element being independently actuatable and being designed to deform said wall in a direction that extends radially in relation to said axis (X) and is angularly centered in relation to its angular sector, under the effect of a predetermined voltage command.

Classes IPC  ?

• F02K 1/10 - Variation de la section utile de la tubulure de jet ou de la tuyère par déviation de la tubulure de jet ou de la tuyère
• B64D 27/16 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction
• B64C 15/02 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant des jets propulsifs
• B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
• B64C 27/20 - Giravions caractérisés par le fait qu'ils possèdent des rotors haubanés, p.ex. plates-formes volantes
• B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
• F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
• F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet