Abstract

A propulsion unit for an aircraft includes an engine pylon, a turbine engine fixed to the engine pylon, and a cowling. The turbine engine includes a fluidic system, and the cowling has at least one panel that is pivotably connected to the engine pylon and carries at least one surface heat exchanger. The surface heat exchanger includes a fluidic circuit connected to the fluidic system by at least one telescopic link.

IPC Classes  ?

• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• B64D 29/06 - Attaching of nacelles, fairings, or cowlings

Abstract

A digital system for determining at least one faulty component of an aircraft including: a first module for determining at least one first symptom of the aircraft from status data collected on-wing; a second module for determining at least one second symptom of the aircraft from degradation data representative of an abnormal variation in flight data; a module for determining failure probabilities of a plurality of aircraft components on the basis of the at least one first and second symptoms, the module including a Bayesian network trained using a knowledge base including data produced by a natural language processing module configured to process aircraft maintenance reports, a module configured to signal at least one faulty component among the plurality of components as a function of said probabilities.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• G06N 7/01 - Probabilistic graphical models, e.g. probabilistic networks
• G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time

Abstract

An aeronautical propulsion unit having a longitudinal axis and an upstream rotor row and a downstream stator row of unducted blades. In the downstream state row, at least two stator blades are at different axial positions relative to one another along the longitudinal axis of the propulsion unit.

IPC Classes  ?

• B64C 11/18 - Aerodynamic features
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

A system for electronically actuating a load, includes a control module; a transistor configured to be actuated by the control module by an electrical command in order to modify a load level; a monitoring module configured to determine a monitoring state depending on the load level, and to transmit the monitoring state to the control module; a filtering module configured to apply a delay to an evaluation of the activation or deactivation state of the load by the monitoring module: a relaxation module intended to protect the actuating system against an over-current by generating a plurality of relaxation oscillations at a terminal of the load, each relaxation oscillation being produced by: activating the transistor in a linear operation mode for an activation time determined by the relaxation module; and opening the transistor for a deactivation time determined by the relaxation module, successively to the activation time.

IPC Classes  ?

• H02H 1/04 - Arrangements for preventing response to transient abnormal conditions, e.g. to lightning
• H02H 1/00 - Details of emergency protective circuit arrangements
• H02H 3/08 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current

Abstract

A method for assisting in landing of an aircraft includes synchronizing an on-board system and a ground system by exchanging an item of timestamp item of information between the ground system and the on-board system, estimating an item of information characteristic of the distance separating the aircraft from a sub-module of the ground system, and combining the information to infer therefrom an item of information characteristic of the raw general direction of arrival of the aircraft, estimating an item of information characteristic of the direction of a signal transmitted by the aircraft with respect to the ground system, comparing the item of information characteristic of the raw general direction of arrival of the aircraft with the item of information characteristic of the direction, and determining an item of information characteristic of the refined general direction of arrival of the aircraft with respect to the given point in the landing zone.

IPC Classes  ?

• G08G 5/26 - Transmission of traffic-related information between aircraft and ground stations
• G01S 13/46 - Indirect determination of position data
• G05D 1/247 - Arrangements for determining position or orientation using signals provided by artificial sources external to the vehicle, e.g. navigation beacons
• G05D 1/654 - Landing
• G05D 109/25 - Rotorcrafts
• G08G 5/54 - Navigation or guidance aids for approach or landing
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 9/16 - Resonant antennas with feed intermediate between the extremities of the antenna, e.g. centre-fed dipole
• H01Q 21/00 - Antenna arrays or systems
• H04J 3/06 - Synchronising arrangements
• H04W 56/00 - Synchronisation arrangements

Abstract

An open rotor propulsion system includes a fan section including an unducted rotating element and a non-rotating stationary element, a forward frame housing an inlet duct, a ducted fan positioned within the inlet duct, a fan duct and a core duct extending aft the ducted fan, an engine positioned within the core duct and including low-and high-pressure compressors, an intermediate case between the low-and high-pressure compressors, a fan drive turbine and a shaft to drive the ducted fan, and four bearings that support the shaft. The four bearings include a first bearing connected to the forward frame or the intermediate case, and a second bearing aft of the first bearing and including a gravity center axially positioned between a first plane that includes a gravity center of the low-pressure compressor and a second plane that includes a gravity center of the intermediate case.

IPC Classes  ?

• B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
• B64D 27/40 - Arrangements for mounting power plants in aircraft
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64F 5/40 - Maintaining or repairing aircraft
• F02C 7/06 - Arrangement of bearingsLubricating
• F16C 19/49 - Bearings with both balls and rollers
• F16C 33/38 - Ball cages

Abstract

The invention relates to an electrically insulating material (1) comprising a polymer matrix (11) containing a polymer or a polymer blend in which inorganic particles (12) are dispersed. The inorganic particles are hollow.

IPC Classes  ?

• H01B 3/30 - Insulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances plasticsInsulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances resinsInsulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances waxes
• C08K 7/24 - Expanded, porous or hollow particles inorganic
• C08K 7/26 - Silicon-containing compounds
• C08K 3/36 - Silica
• H01B 7/28 - Protection against damage caused by external factors, e.g. sheaths or armouring by moisture, corrosion, chemical attack or weather

Abstract

The invention relates to an assembly (15) for an aircraft propulsion unit, comprising - a radial delimitation structure (34) for the circulation of a gas flow (12b), having a radial delimitation surface (34a); - and a heat exchanger (45a) which projects from the radial delimitation surface (34a) and through which a first part (12b1) of the gas flow is designed to pass, the exchanger further comprising a cowling (50), an upstream inlet (52) and a downstream outlet (54). The cowling (50) comprises: - an intermediate inlet (52a) through which a sample (P1) from the second part (12b2) of the gas flow is intended to pass; - and an intermediate outlet (54a) through which a primary portion (12b1a) of the first part (12b1) is intended to pass, the sample (P1) and a secondary portion (12b1b) of the first part (12b1) being extracted via the outlet (54).

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange

Abstract

The invention relates to a method for monitoring an oil pressure in an oil circuit of an aircraft engine on the basis of a previously generated normalisation model, the monitoring method including the steps of: - obtaining at least one sample of current values, each sample including a current oil temperature value associated with a current oil pressure value and with a current high-pressure engine speed value, which values are acquired during a flight of the aircraft; - for each sample, providing the current oil temperature, oil pressure and high-pressure engine speed values to the normalisation model so as to obtain a normalised oil pressure value for the sample; and - comparing the normalised oil pressure value(s) with at least one threshold beyond or below which the oil pressure in the oil circuit of the engine is considered to be abnormal.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• F01M 11/10 - Indicating devicesOther safety devices
• F02C 7/14 - Cooling of plants of fluids in the plant

Abstract

The present disclosure relates to a seal assembly (10), comprising: - a rotor (30),- an annular seal (20), the annular seal (20) comprising a radially inner surface (S1) radially facing the radially outer surface (S2) of the rotor, the radially inner surface (S1) of the annular seal (20) comprising a longitudinal annular portion with limited radial contact (S11) defining a first radial clearance (J1) between the longitudinal annular portion with limited radial contact (S11) and the radially outer surface (S2) of the radially facing rotor, characterised in that the radially inner surface (S1) comprises at least one longitudinal portion with preferential radial contact (S12) defining a second radial clearance (J2) between the at least one longitudinal portion with preferential radial contact (S12) and the radially outer surface (S2) of the radially facing rotor, the second radial clearance (J2) being less than the first radial clearance (J1).

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Abstract

A computer-implemented method for detecting the presence of an electric arc on a power line using a machine learning algorithm, carried out using a time-correlated measurement of the arc voltage Varc, of the current I and of the source voltage Vsource and also a knowledge model for linking the arc voltage Varc and the current I to constants depending on the knowledge model, implemented after a learning phase that involves adjusting a learning model that takes the current I and the source voltage Vsource at input and provides the voltage Varc and the constants of the knowledge model at output; the method including continuously detecting the presence of an arc using a decision function depending on a cost function used in the learning phase.

IPC Classes  ?

• G01R 31/12 - Testing dielectric strength or breakdown voltage
• H02H 1/00 - Details of emergency protective circuit arrangements

Abstract

An electrical system for a gas turbine engine includes a power supply bus, first and second converters, and a monitoring device connected to the first and second converters. The monitoring device receives a monitoring signal representative of a correction associated with a difference between a measurement of a voltage of the bus and a reference, performs a frequency filtering of the monitoring signal to determine low and high frequency components, pilots the first converter to compensate for a change in a voltage of the bus and being implemented from a first part of the low-frequency component and a first part of the high-frequency component, and pilots the second converter to compensate for the change in the voltage of the bus and being implemented from a second part of the low-frequency component and a second part of the high-frequency component.

IPC Classes  ?

• H02M 7/04 - Conversion of AC power input into DC power output without possibility of reversal by static converters
• B64D 41/00 - Power installations for auxiliary purposes
• F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
• G01R 19/10 - Measuring sum, difference, or ratio
• G01R 31/40 - Testing power supplies
• H02M 1/44 - Circuits or arrangements for compensating for electromagnetic interference in converters or inverters

Abstract

An assembly for a turbine engine including an intermediate casing with a primary duct portion, a tertiary duct portion, an intermediate hub, an inter-duct shroud, an outer shroud, structural arms connecting the intermediate hub and the outer shroud, and an exhaust duct extending between the primary duct and the tertiary duct, and bypass valves capable of drawing fluid from the primary duct portion in order to direct it toward the exhaust duct. The intermediate casing is formed as a single piece and has a cavity located between the intermediate hub and the inter-duct shroud that opens onto the upstream face of the intermediate casing via an opening, wherein the bypass valves are able to be inserted into the cavity via the opening.

IPC Classes  ?

• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows

Abstract

A guide device for an aircraft turbine engine, the guide device includes a metal body provided with at least one attachment tab including an opening configured to receive a screw or the like; a guide pad made of a plastic or composite material, this pad provided with a first surface bonded to a first surface of the body and a second opposing surface which is free and which is configured to form a sliding guide surface, wherein the metal body includes through-holes which open onto the first surface of the body and in that the guide pad includes studs which project from the first surface of the pad and which are respectively engaged and crimped in the holes of the body.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

Abstract

A designation system includes a laser designator and an apparatus for tracking a designation of a target. The apparatus includes an optronic device (4) having an optical imaging sensor (5), the sensor being an on-silicon sensor, and the apparatus has sensor control means capable of modifying at least one parameter of the sensor in order, during operation, to image at least one designation mark generated by the laser designator per predetermined given time interval, which repeats periodically, the apparatus being asynchronous with the laser designator.

IPC Classes  ?

• F41G 7/22 - Homing guidance systems
• F41G 3/14 - Indirect aiming means
• G06T 7/70 - Determining position or orientation of objects or cameras
• H04N 23/55 - Optical parts specially adapted for electronic image sensorsMounting thereof
• H04N 23/60 - Control of cameras or camera modules

Abstract

The present disclosure relates to a shim (50) for a turbomachine rotor blade (40) comprising a blade root (41) accommodated in a recess (31) of a rotor disk (30). The recess comprises a first cavity (311) and a second cavity (312) arranged radially separated from each other by two first bearing seats (32a, 32b) of the rotor disk arranged circumferentially facing each other in such a way as to define between them a longitudinal opening (33). The shim comprises a flexible body (51), a first pad (52) and a second pad (53) which each project radially on either side of the flexible body. In a mounted configuration of the shim, the flexible body is mounted radially between the blade root and the two first bearing seats. The first pad bears against the blade root, and the second pad against a radially outer surface (S3a, S3b) of the two first bearing seats. A stop (54) also projects radially from the flexible body and passes through the longitudinal opening into the second cavity. An assembly (100) for a turbomachine comprises the rotor disk, the rotor blade and the shim.

IPC Classes  ?

• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

The present disclosure relates to a turbomachine rotor disk (30) centered on a longitudinal axis (X) and comprising a recess (31) configured to accommodate a blade root (41) of a rotor blade (40) and a shim (50). The recess comprises a first cavity (311) which emerges at a radially outer periphery (S1) of the rotor disk and which is configured to accommodate the blade root and the shim, and a second cavity (312) arranged such that the first cavity and the second cavity are separated radially from each other by two first bearing seats (32a, 32b) of the rotor disk which extend circumferentially respectively from two opposite and mutually facing circumferential end faces (S2a, S2b) of the recess and which each extend longitudinally along a corresponding circumferential end face of the recess. The two first bearing seats each comprise a radially outer surface (S3a, S3b) configured to serve as radial support for the blade root via the shim. The two first bearing seats are arranged circumferentially facing each other in such a way as to define between them a longitudinal opening (33) which emerges at one end into the first cavity and at the other end into the second cavity. An assembly (100) for a turbomachine comprises the rotor disk, the rotor blade and the shim. The shim comprises a flexible body (51) mounted radially between the blade root and the two first bearing seats, and at least one stop (54) which radially projects from the flexible body. The at least one stop (54) passes through the longitudinal opening into the second cavity. A turbomachine (1) comprises the assembly.

IPC Classes  ?

• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Goods & Services

Appareils et instruments scientifiques, de recherche, de mesurage, de détection, d’essais; Appareils et instruments pour la conduite, la distribution, la transformation, l'accumulation, le réglage ou la commande de la distribution ou de la consommation d’électricité; Appareils et instruments pour l'enregistrement, la transmission, la reproduction ou le traitement de données; Appareils et dispositifs électroniques pour la régulation de la température corporelle; systèmes portables et fixes de thermorégulation active chaud/froid; capteurs et commandes électroniques pour la gestion de la température; logiciels pour le contrôle et l'ajustement des dispositifs de thermorégulation; Capteurs; capteurs thermiques et de température; Capteurs d'humidité; batteries; Semi-conducteurs; Circuits intégrés; Puces informatiques; Logiciels informatiques; Dispositifs électroniques de surveillance pour la détection, le stockage, la communication, le suivi, le téléchargement de données; Combinaisons thermiques pour pilotes d’aéronefs, d’automobiles ou de tout autre véhicule; Equipements de protection personnelle incorporant des dispositifs de thermorégulation; Equipements de plongée notamment combinaisons et accessoires incorporant des dispositifs de thermorégulation. Appareils et instruments médicaux et paramédicaux pour la régulation de la température corporelle; systèmes de thermorégulation portables ou intégrés à des sièges, coussins, literie, mobiliers ou tout autre support, destinés aux soins de santé ou au confort des utilisateurs. Appareils de chauffage, de refroidissement et de climatisation; systèmes de thermorégulation actifs pour le corps humain; dispositifs portables ou fixes pour le contrôle du confort thermique; équipements intégrés à du mobilier (sièges, fauteuils, etc.) ou portés sur le corps, permettant la régulation de la température. Dispositifs de thermorégulation pour véhicules, notamment pour sièges, coussins et habitacles d’aéronefs, d’automobiles ou tout autre véhicule de transport terrestre, aérien et maritime; Dispositifs de thermorégulation pour landaus, sièges de sécurité pour enfants, voitures d'enfants, poussettes. vêtements, couvertures et accessoires pour animaux incorporant des dispositifs de thermorégulation. Mobilier incorporant des dispositifs de thermorégulation; fauteuils, coussins, sièges, literie, matelas, et tout meuble incorporant des dispositifs de thermorégulation; meubles, niches, couchettes et paniers pour animaux. Vêtements, articles vestimentaires et accessoires équipés de dispositifs de thermorégulation active chaud/froid; vêtements chauffants ou refroidissants, accessoires portables pour la régulation thermique. Services scientifiques et technologiques ainsi que services de recherches et de conception y relatifs; Conception et développement de systèmes de thermorégulation; prestations de conseil technique en matière de confort thermique; conception et développement de logiciels pour la gestion de dispositifs de thermorégulation.

Abstract

A method for producing a plurality of blades having a first height includes providing a mold having an internal cavity bounded by an internal side face of the mold which is axisymmetric about a longitudinal axis, the side face extending along the longitudinal axis to a second height which is greater than or equal to first height, the side face defining a plurality of sections perpendicular to the longitudinal axis, which have a radius for each section. The ratio of the height of the side face to the radius of the section is less than or equal to 2.0. The method also includes rotating the mold about the longitudinal axis at a rotation speed of between 200 rpm and 800 rpm, and pouring a material into the internal cavity in order to form, by centrifugation, a tubular part along the longitudinal axis.

IPC Classes  ?

• B22D 13/02 - Centrifugal castingCasting by using centrifugal force of elongated solid or hollow bodies, e.g. pipes, in moulds rotating around their longitudinal axis
• F01D 5/14 - Form or construction

Abstract

An assembly for an aircraft turbine engine is disclosed. The aircraft turbine engine has a longitudinal axis and a distributor which has a ring of stator vanes including a foot at the radially inner end of the distributor, foot having an annular seal configured to engage in a non-contact sealing manner with a cylindrical shroud of a rotor of the turbine engine where the shroud is arranged radially under the distributor. The assembly includes the seal having a plurality of seal segments distributed circumferentially about the longitudinal axis, each seal segment including a radially outer annular wall segment and a radially inner annular wall segment connected to each other by an elastically deformable member, wherein each radially outer annular wall segment is attached to a seal support.

IPC Classes  ?

• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

An assembly for an aircraft turbine engine having a longitudinal axis includes a distributor having a stator vane ring with a foot at the radially inner end of the distributor, the foot carrying an annular seal configured to cooperate in a non-contact sealing manner with a cylindrical rotor shroud of the turbine engine, the turbine engine being arranged radially under the distributor. The seal includes a plurality of seal segments distributed circumferentially about the longitudinal axis, each seal segment including a radially outer annular wall segment and a radially inner annular wall segment which are connected to each other by an elastically deformable member, wherein each radially outer annular wall segment is fixed to a seal support.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F16J 15/44 - Free-space packings

Abstract

A seal for an aircraft turbine engine comprising a plurality of seal segments distributed circumferentially about a longitudinal axis, each seal segment having a radially outer annular wall segment and a radially inner annular wall segment which are connected to each other by an elastically deformable member. The elastically deformable member includes an inner leg having a radially inner end fixed to the radially inner annular wall segment and an outer leg having a radially outer end fixed to the radially outer annular wall segment, the radially outer end of the inner leg and the radially inner end of the outer leg being connected to each other by a connecting wall, the inner leg and the outer leg extending radially such that the radially inner end of the outer leg is arranged radially inside the radially outer end of the inner leg.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type

Abstract

A device for protecting against fast overvoltages and slow overvoltages placed in parallel with an alternating-current generation line includes: a first current source including an input and an output, the input of the first current source being connected to a first terminal of the generation line, a second current source including an input and an output, the input of the second current source being connected to a second terminal of the generation line, the output of the second current source being connected to the output of the first current source.

IPC Classes  ?

• H02H 9/04 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess voltage
• G01R 31/42 - AC power supplies
• H02H 1/00 - Details of emergency protective circuit arrangements

Abstract

The invention relates to a method for assisting in the diagnosis of an aeronautical system (20), the aeronautical system (20) comprising a set of equipment, the method comprising automatically processing a document (x) describing a failure of the aeronautical system, the method further comprising providing the document to a predictive model (11) suitable for providing a classification vector, each component of which associates a score with a class, and providing said vector to a conformal prediction module (12) suitable for determining a set of combinations of classes characterising the failure and for implementing steps of generating candidate combinations and selecting the combinations satisfying a comparison criterion, wherein the step of generating combinations comprises constructing a tree whose nodes correspond to the candidate combinations, the construction comprising comparing a lower bound of the non-conformity score for a node with the quantile, and generating the descendants of the node only if said lower bound is less than or equal to the quantile.

IPC Classes  ?

• G06Q 10/04 - Forecasting or optimisation specially adapted for administrative or management purposes, e.g. linear programming or "cutting stock problem"
• G06Q 10/20 - Administration of product repair or maintenance
• G06Q 50/40 - Business processes related to the transportation industry

Abstract

The invention relates to a method (100) for producing an anti-wear coating for a part made of organic matrix composite materials. The method (100) comprises: - carrying out physical vapour deposition (101) of an anti-wear functional layer such as titanium nitride or tungsten-doped hydrogenated carbon on a first face of a metal substrate; - preparing (103) the surface of a second face, opposite the first face, of the metal substrate; - preparing (109) the surface of a contact area of an outer surface of the part; - draping (111) a film adhesive layer over the contact area; - positioning (113), on the film adhesive layer, the metal substrate covered with the thin layer; and, - polymerising (115) the film adhesive layer.

IPC Classes  ?

• C23C 14/02 - Pretreatment of the material to be coated
• C23C 14/06 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
• C09J 5/02 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving pretreatment of the surfaces to be joined
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

Method for the automated weaving of a woven structure (30) by means of a weaving machine (1), comprising the insertion of a weft thread during the opening of a shed of warp threads, and prior steps of optimization, by an optimization tool (20), of an objective function having a first member evaluating the balance of said warp threads during the shed opening, said balance of the warp threads being evaluated by differences in elongation between the warp threads of an upper opening (10a) of said shed, and of a lower opening (10b) of said shed, and a second member evaluating constraints specific to the weaving machine (1). This optimization comprises the determination of a set of opening parameters that, at least locally, minimize said objective function, and this set of opening parameters is used to set the parameters of the weaving machine (1).

IPC Classes  ?

• D03D 49/14 - Compensating for tension differences during shedding
• D03D 41/00 - Looms not otherwise provided for, e.g. for weaving chenille yarnDetails peculiar to these looms

Abstract

The invention relates to a metal powder for a metal injection moulding method, the metal powder being formed of a cobalt-based alloy comprising: —between 23.00 wt % and 24.25 wt% chromium; —between 9.00 wt % and 11.00 wt % nickel; —between 6.50 wt % and 7.50 wt % tungsten; —between 3.00 wt % and 4.00 wt % tantalum; —between 0.45 wt% and 0.60 wt % carbon; —between 0.30 wt % and 0.50 wt % zirconium; —between 0.15 wt % and 0.25 wt % titanium; —at most 2.00 wt % iron; —at most 0.30 wt % silicon; —at most 0.10 wt % manganese; —at most 0.10 wt % copper; —at most 0.015 wt % sulphur; —at most 0.015 wt % phosphorus; —at most 0.010 wt % boron; —at most 200 ppm oxygen; —at most 200 ppm nitrogen; —at most 100 ppm hydrogen.

IPC Classes  ?

• B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
• B22F 3/10 - Sintering only
• B22F 3/15 - Hot isostatic pressing
• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor for producing castings from a slip
• B22F 3/24 - After-treatment of workpieces or articles
• B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
• C22C 19/07 - Alloys based on nickel or cobalt based on cobalt

Abstract

A tool for bonding at least one anti-wear strip to a turbomachine blade comprising: —a support, —at least one first fastening member which is fastened to the support and is able to cooperate with the root of the blade in order to immobilize it with respect to the support and —at least one second member for holding said at least one anti-wear strip on the blade and for heating this anti-wear strip for the bonding thereof, this second member being fastened to the support and comprising, on the one hand, at least one expandable bag, and, on the other hand, at least one heating element able to heat said at least one anti-wear strip for the bonding thereof.

IPC Classes  ?

• B29C 65/22 - Heated wire
• B23Q 3/06 - Work-clamping means
• B29C 65/00 - Joining of preformed partsApparatus therefor
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

An oil tank for an aircraft turbomachine, including: an enclosure capable of containing the oil and having a main axis intended to be oriented vertically in the mounting position; an oil inlet at an upper part of the enclosure; an oil outlet at a lower part of the enclosure. The oil tank further includes: a wheel arranged in the lower part of the enclosure and capable of being driven in rotation by drive means so as to centrifuge the oil against a retaining wall of the enclosure and against the oil outlet, and thus maintain an oil supply to said oil outlet during flight phases of the aircraft in zero or negative gravity.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• F01D 7/00 - Rotors with blades adjustable in operationControl thereof
• F01D 25/18 - Lubricating arrangements
• F15B 1/26 - Supply reservoir or sump assemblies

Abstract

The present invention relates to a method and system for managing the drawing of mechanical power from a two-spool or three-spool turbine engine (1) for an aircraft, in which at least two electric machines (3, 4) are suitable for recovering mechanical energy, one from a shaft driven by one of the turbines of the turbine engine (1), the other from a shaft driven by another turbine, in which the distribution of the drawing between one and the other of the two electric machines (3, 4) is controlled dynamically according to the phases of flight.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

Abstract

A seal for an aircraft turbine engine includes a plurality of seal segments that are circumferentially distributed about a longitudinal axis. Each seal segment has a radially outer annular wall segment and a radially inner annular wall segment which are connected to each other by an elastically deformable member. The radially outer annular wall segments form a monolithic outer shroud, and the radially inner annular wall segments are arranged circumferentially end-to-end. Each radially inner annular wall segment has a first circumferential edge and an opposite second circumferential edge which each has a slit. A tongue is mounted in part at the junction of two facing circumferential edges.

IPC Classes  ?

• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Abstract

The invention relates to a tool (1) for bonding a thermoplastic polymer film (3) to a vane (2) of an aircraft turbine engine, the tool comprising a mould (6) that includes a cavity (8) configured to receive the vane (2) or the blade at least partially covered with the thermoplastic polymer film (3), a heating device (9, 10) intended to cover at least part of a surface (4) of the vane (2) or of the blade opposite the bottom of the cavity (8), a draining fabric layer (11) intended to cover the heating device (9, 10), a vacuum bag (12) intended to cover at least the draining fabric layer (11) and configured to apply a vacuum within the cavity (8), and a pressurising device (13') intended to apply a pressure to the vacuum bag (12).

IPC Classes  ?

• B29C 65/18 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool
• B29C 65/30 - Electrical means
• B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
• B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

The invention relates to a tool (1) for bonding a thermoplastic polymer film (3) to a vane (2) of an aircraft turbine engine, the tool comprising a mould (6) that includes a cavity (8) configured to receive the vane (2) or blade at least partially covered with the thermoplastic polymer film (3), a draining fabric layer (11) intended to cover the thermoplastic polymer film (3), a vacuum bag (12) intended to cover at least the draining fabric layer (11) and configured to apply a vacuum within the cavity (8), a pressurising device (13') intended to apply a pressure to the vacuum bag (12), and a heating device configured to receive the mould (6).

IPC Classes  ?

• B29C 65/18 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool
• B29C 65/30 - Electrical means
• B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
• B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A turbomachine stator extending about a central axis and including an inner wall and an outer wall delimiting an annular flow passage, a plurality of variable-pitch vanes, each vane extending radially in the annular flow passage between a base movably fixed to the outer wall, and a free end, the inner wall including a main profile and at least one circular platform arranged opposite the free end of one of the vanes, the platform including a main surface and at least one longitudinal groove, the platform being movable in rotation relative to the main profile between a first position in which a main axis of the groove is substantially parallel to the central axis, and at least a second position in which the main axis is transverse to the central axis.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

An aircraft part includes a composite material structure including a fibrous reinforcement and matrix, the fibrous reinforcement being embedded into the matrix, and heating elements that heat the aircraft part, each of the heating elements being embedded into the matrix of the composite material structure and being distributed across the aircraft part with a density depending on a position in the aircraft part.

IPC Classes  ?

• F01D 25/02 - De-icing means for engines having icing phenomena
• B64C 11/26 - Fabricated blades
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method for achieving inertial localization of a carrier using a stochastic filter of recursive-Bayesian type implemented by an inertial localization device, the method including a plurality of cycles, each cycle including a propagation procedure and, when a measurement is available, an updating procedure, in which method, in the propagation procedure, the propagation is performed using a propagation model taking into account at least one component of a matrix of the spatial gradients of the gravity vector, which matrix is delivering using an enriched gravimetric model.

IPC Classes  ?

• G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation

Abstract

The invention relates to a shell (1) for fabricating at least one single-crystal component by molding using a removable material, comprising a central casting pit (11) configured for introduction of molten metal therein, the shell (1) comprising at least one mold (12) arranged around the central pit (11), each mold (12) comprising an inner cavity (121) in fluidic communication with the central pit (11), the cavity (121) being configured so that the molten metal fills the cavity (121) and forms a component, the shell (1) comprising at least one generally annular heat shield (13) arranged around the central pit (11), the at least one heat shield (13) further comprising an outer wall (131) at least partially covered with an outer coating (135) having a surface roughness Ra less than 5 µm and an emissivity E greater than 0.6 when measured at a temperature between 1400 and 1600°C.

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/04 - Use of lost patterns
• B22C 9/08 - Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
• B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles
• B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould

Abstract

A serial data bus asynchronous communication system (100) includes a bus controller, BC, module (102) in signal communication with a bus network (101,103,105) and a remote terminal, RT, module (150) in signal communication with the bus network (101, 103, 105) to exchange data with the BC module (102). The RT module (150) includes a RT controller (152) implemented with a read/write serial peripheral interface, SPI, (160) and a timing controller (162) in signal communication (168) with the read/write SPI (160). The read/write serial peripheral SPI (160) manages transfer of the data. The timing controller (162) determines an active data access of the RT module (150) by the BC module (102) and outputs a trigger signal (166) indicating the active data access, and the read/write SPI (160) manages the transfer of the data based on the trigger signal (166).

IPC Classes  ?

• G06F 13/38 - Information transfer, e.g. on bus
• G06F 13/40 - Bus structure
• G06F 13/42 - Bus transfer protocol, e.g. handshakeSynchronisation
• H04L 12/40 - Bus networks
• G06F 13/12 - Program control for peripheral devices using hardware independent of the central processor, e.g. channel or peripheral processor
• G06F 13/362 - Handling requests for interconnection or transfer for access to common bus or bus system with centralised access control
• H04L 12/417 - Bus networks with decentralised control with deterministic access, e.g. token passing
• H04Q 9/04 - Arrangements for synchronous operation

Abstract

An aircraft propulsion system including a gas turbine engine with a combustion chamber and an engine spool, the engine spool including a turbine downstream of the combustion chamber, a compressor upstream of the combustion chamber and a transmission shaft; a control system; a member for determining a current engine speed of the engine spool; and a rotary machine for generating electrical power removing mechanical power from the transmission shaft. The control system limits a current electrical power generated by the rotary machine, at least when the engine spool is in the acceleration phase, to a maximum authorized power, the maximum authorized power being a function of the current engine speed before acceleration, and the propulsion system includes a device for determining the current electrical power and the control system establishes the engine speed above an idle speed which is a function of the current electrical power.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators

Abstract

A module for a turbine engine, in particular for an aircraft turbine engine, includes a shaft extending in an axial direction and an electric machine including a rotor rotatably coupled to the shaft of the module, the rotor comprising a disc and magnetic elements arranged regularly around the periphery of the disc; and a stator rigidly attached to a casing of the module including a ring and coils distributed annularly inside the ring of the stator, the coils being arranged outside the magnetic elements of the rotor in a radial direction, wherein each coil is radially movable between a first end position and a second end position, each coil being held in the first position in normal operation and moved toward the second end position in the event of the rotor moving radially towards the coil of the stator.

IPC Classes  ?

• H02K 1/12 - Stationary parts of the magnetic circuit
• H02K 1/22 - Rotating parts of the magnetic circuit
• H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines

Abstract

A seal for an aircraft turbine engine includes a plurality of seal segments distributed circumferentially about a longitudinal axis, each seal segment having a radially outer annular wall segment and a radially inner annular wall segment which are connected to each other by an elastically deformable member. Pairs of circumferentially adjacent seal segments have their respective elastically deformable member implemented monolithically as a common deformable elastic member, the common deformable elastic member connecting together two radially inner annular wall segments of circumferentially-adjacent seal segments such that the radially outer annular wall segments of the seal segments form a monolithic outer shroud.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F16J 15/44 - Free-space packings

Abstract

The invention relates to a shell (1) for fabricating at least one single-crystal component by molding using a removable material, comprising a central casting pit (11) configured for introduction of molten metal therein, the shell (1) comprising at least one mold (12) arranged around the central pit (11), each mold (12) being configured such that the molten metal fills a cavity (121) in a main filling direction and forms a component, the shell (1) comprising at least one heat shield (13) arranged in the vicinity of the at least one mold (12) and extending substantially in the filling direction along the at least one mold (12), the at least one heat shield (13) further comprising an outer wall (131) having a surface roughness Ra less than 5 µm and an emissivity E greater than 0.6 when measured at a temperature between 1400 and 1600°C.

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/04 - Use of lost patterns
• B22C 9/08 - Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
• B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles
• B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould

Abstract

(X'i(k))Pref(l + 1))XY ri-(k), (pφi(k)Xi(k),yi(k)(&φrefij(l))(Δφij(l))(φij(l))(X'i(l + 1))(φrefij(l))φrefij(l)), for all pairs of aircraft.

IPC Classes  ?

• G05D 1/46 - Control of position or course in three dimensions
• G05D 1/646 - Following a predefined trajectory, e.g. a line marked on the floor or a flight path
• G05D 1/695 - Coordinated control of the position or course of two or more vehicles for maintaining a fixed relative position of the vehicles, e.g. for convoy travelling or formation flight
• G05D 1/698 - Control allocation
• G05D 109/22 - Aircraft, e.g. drones with fixed wings
• G01C 21/34 - Route searchingRoute guidance
• G08G 5/56 - Navigation or guidance aids for two or more aircraft

Abstract

The invention relates to a composition of a nickel superalloy consisting of: - an aluminum content by mass of between 0% and 0.5%, - a cobalt content by mass of between 0% and 12%, - a chromium content by mass of between 14% and 20%, - an iron content by mass of between 0% and 10%, - a molybdenum content by mass of between 0% and 2%, - a niobium content by mass of between 0% and 1%, - a tantalum content by mass of between 13% and 17%, - a titanium content by mass of between 0% and 1%, - a tungsten content by mass of between 0% and 3%, - a carbon content by mass of between 0% and 0.05%, - a manganese content by mass of between 0% and 0.5%, - a silicon content by mass of between 0% and 0.5%, as well as unavoidable impurities and the balance being nickel.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• B22F 10/20 - Direct sintering or melting

Abstract

The invention relates to a turbomachine compressor casing comprising an inner annular wall (101) and an outer annular wall (102) delimiting between them an annular cavity (150) extending in length in an axial direction (DA) between a front bottom (151) and a rear bottom (152) and in height in a radial direction (DR) between an inner face (1021) of the outer annular wall and an outer face (1011) of the inner annular wall, the inner annular wall of the casing comprising a plurality of slots (110) which open into the annular cavity, are arranged one next to the other in a circumferential direction (DC) and extend in length in the axial direction between the front bottom and the rear bottom and in height in the radial direction, characterized in that, in the axial direction, the annular cavity comprises a first portion (155) situated above, in the radial direction, an upstream part of the slots and a second portion (156) situated downstream of the first portion, the height of the annular cavity in the first portion (H155) being greater than that of the second portion (H156).

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers

Abstract

A method for detecting an anomaly in a plurality of predefined zones of a single aeronautical component includes supplying an image to be inspected to a detection system that includes a backbone neural network configured to supply an intermediate representation of the image to be inspected, and localisation neural networks that are respectively associated with the zones and each designed, on the basis of the intermediate representation, to search for one or more anomalies and to locate each anomaly found in the image to be inspected. The detection system has been previously trained, for each zone, by a step of supplying, to the backbone network, training images, and, on the basis of the training images of the relevant zone, an adaptive adjustment step during which parameters of the backbone network and of the localisation network that is associated with the relevant zone are adjusted.

IPC Classes  ?

• G06T 7/00 - Image analysis
• G06V 10/25 - Determination of region of interest [ROI] or a volume of interest [VOI]
• G06V 10/762 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using clustering, e.g. of similar faces in social networks
• G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
• G06V 10/774 - Generating sets of training patternsBootstrap methods, e.g. bagging or boosting
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks

Abstract

A bladed turbomachine assembly extends about an axis (AX) and includes disc carrying blades (21a-21d), wherein each blade (21a-21d) extends radially from a root by which it is rigidly connected to the disc to a heel including a platform (26a-26d). The assembly includes an alternation of blades (21a, 21c) prestressed towards upstream and blades (21b, 21d) prestressed towards downstream, each blade (21a, 21c) prestressed towards upstream having its heel (24c) tending to shift towards upstream, each blade (21b, 21d) prestressed towards downstream having its heel (24b) tending to shift towards downstream. A bladed turbomachine assembly extends about an axis (AX) and includes disc carrying blades (21a-21d), wherein each blade (21a-21d) extends radially from a root by which it is rigidly connected to the disc to a heel including a platform (26a-26d). The assembly includes an alternation of blades (21a, 21c) prestressed towards upstream and blades (21b, 21d) prestressed towards downstream, each blade (21a, 21c) prestressed towards upstream having its heel (24c) tending to shift towards upstream, each blade (21b, 21d) prestressed towards downstream having its heel (24b) tending to shift towards downstream. The pairs of circumferentially adjacent blades have platforms (26a-26d), contiguous circumferential ends of which (27b-27d, 28a-28c) include protrusions (29a-29c) and notches (31b-31d) fitting together. A bladed turbomachine assembly extends about an axis (AX) and includes disc carrying blades (21a-21d), wherein each blade (21a-21d) extends radially from a root by which it is rigidly connected to the disc to a heel including a platform (26a-26d). The assembly includes an alternation of blades (21a, 21c) prestressed towards upstream and blades (21b, 21d) prestressed towards downstream, each blade (21a, 21c) prestressed towards upstream having its heel (24c) tending to shift towards upstream, each blade (21b, 21d) prestressed towards downstream having its heel (24b) tending to shift towards downstream. The pairs of circumferentially adjacent blades have platforms (26a-26d), contiguous circumferential ends of which (27b-27d, 28a-28c) include protrusions (29a-29c) and notches (31b-31d) fitting together. Each protrusion (29a-29c) is pressed into a notch (31b-31d) receiving it according to the axial direction (AX) by the prestresses of the blades that carry them.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

The invention relates to a variable-pitch blade (7) for a turbine engine, the blade comprising: - a tubular metal sleeve (13) comprising an opening (17) extending through the sleeve (13) along a pitch axis (Y), the opening (17) being delimited by an internal wall of the sleeve (13); - a fibrous structure (20) comprising a blade root (22), the blade root (22) comprising a tubular attachment portion (23) inserted axially into the opening (17) of the sleeve (13), this attachment portion (23) comprising a housing (20a) centered on the pitch axis (Y); - a polymerized resin for solidifying the fibrous structure (20) and securing the fibrous structure (20) to the internal wall (18) of the sleeve (13), and - a permanent insert (224) centered on the pitch axis (Y) and inserted axially into the housing (20a) of the attachment portion (23), the permanent insert (224) being separated from the attachment portion (23) by a layer of adhesive (226).

IPC Classes  ?

• B64C 11/06 - Blade mountings for variable-pitch blades
• B64C 11/26 - Fabricated blades
• B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants

Abstract

The invention relates to a rotor blade (20) for an aircraft turbine engine, this blade comprising an airfoil (22) and a root connected to the airfoil by a platform, the airfoil extending from the platform to a free end (22a) comprising a recessed bathtub (36), the rotor blade further comprising an internal circuit (38) for ventilation air to pass therethrough, the internal circuit (38) extending from the root to the free end and opening out through at least one air outlet opening (42) formed in the bottom (44) of the bathtub, the at least one air outlet opening extending along an axis (X) that is not parallel to a longitudinal axis (A) of the airfoil, the at least one opening being oriented toward a wall (33) of a pressure-side face (32) of the airfoil and toward the trailing edge (30) of the airfoil when the opening opens out at the bottom of the bathtub.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• F01D 5/14 - Form or construction

Abstract

The invention relates to a turbine engine (1) of an aircraft (2), comprising: - a gas generator (3) of longitudinal axis (X1) which comprises a power turbine (4); - an unducted fan (5) which is movable about a longitudinal axis (X2) which is parallel to the axis (X1) and offset radially with respect to the axis (X1), the fan (5) being driven by the power turbine (4) via a speed reducer (6) which is arranged radially above an air inlet (7) of the gas generator (3); - an unshrouded stator (8) which is rotationally fixed and arranged axially downstream of the unducted fan (5); characterized in that the stator (8) comprises a ring (9) which supports vanes (10, 11) and which jointly surrounds a casing (12) of the speed reducer (6) and the air inlet (7), the ring (9) being fastened to the casing (12) of the speed reducer (6).

IPC Classes  ?

• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

The present invention relates to a method for manufacturing a fibrous preform of a core for a composite part intended to be articulated with other parts, comprising forming a one-piece strip by three-dimensional weaving, shaping said strip to give it a generally H-shaped cross-section, and positioning a reinforcing counter-form with rounded corners in order to reduce local stress concentrations when the part is under load.

IPC Classes  ?

• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements

Abstract

The invention relates to a fibrous web (10) formed by three-dimensional weaving of first and second yarns, the fibrous web (10) being elongate along a longitudinal axis and comprising a debonding zone (20) present between a first region (11) and a second region (12), the first region comprising woven first lateral portions (11a) connected by a first intermediate portion, the second region comprising second lateral portions (12a) connected by a second intermediate portion (12b) and woven with the first lateral portions, the first yarns extending transversely to the longitudinal axis and comprising a first set (412) extending in the second region and a second set (413) extending in the first region and overlying the debonding zone, the second set (413) crossing the first set (412) in a crossing zone (30) adjacent to the edges (20a) of the debonding zone, so as to extend into the second lateral portions.

IPC Classes  ?

• D03D 1/00 - Woven fabrics designed to make specified articles
• D03D 25/00 - Woven fabrics not otherwise provided for
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements

Abstract

An oil tank for a turbomachine, including an enclosure for the oil, having a main axis, and with walls delimiting a first compartment and a second compartment separated from the first compartment by a separation wall; a channel extending into the first compartment, from the separation wall; an oil inlet mixed with air, arranged on the second compartment; an oil outlet including a conduit extending and opening into the first compartment. The channel extends inside the conduit, so as to ensure oil filling of the conduit and thus maintain an oil supply to the conduit during flight phases in zero or negative gravity.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 25/18 - Lubricating arrangements
• F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
• F01M 11/06 - Means for keeping lubricant level constant or for accommodating movement or position of machines or engines
• F16H 57/04 - Features relating to lubrication or cooling

Abstract

The present disclosure relates to a propulsion assembly (1) comprising: - a main channel (9) which extends between an air inlet (91) and a splitter (92) that divides the main channel (9) into a primary flow path (10) and a cooling flow path (20), - an ejection duct (30) which extends between an ejection inlet (31) that opens into the primary flow path (10) and an ejection outlet (32, 32', 32''), and - a discharge valve (40) which is configured to discharge an air flow into the ejection duct (30), the ejection duct (30) comprising a portion which passes through the cooling flow path (20) such that the ejection outlet (32, 32', 32'') opens out radially outside an external casing of the propulsion assembly (1), the ejection outlet (32, 32', 32'') being located upstream of the outlet of the cooling flow path (20).

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
• F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows

Abstract

The main subject matter of the invention is an assembly (100) for an aircraft turbomachine, comprising a first stator part (2), a second rotor part (3), and a servo-controlled axial seal system (1) comprising a body (7) sliding freely on the first part (2), the assembly defining a main leakage flow path (14) extending from a first enclosure (6) to a second enclosure (5), and the servo-controlled axial seal system comprising a main pressure drop zone (20), as well as a pressure drop initiation zone (30) comprising at least two radial fins (109) spaced axially apart from one another.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F16J 15/447 - Labyrinth packings
• F16J 15/16 - Sealings between relatively-moving surfaces

Abstract

A turbine rotor assembly of a turbine engine includes a rotor disc centred on an X-axis and having recesses, movable blades each including a root mounted in a recess, a plurality of platforms for holding the movable blades in the recesses of the disc, and a flange for holding the movable blades in the recesses, each platform including a duct wall defining a gas flow duct, an L-shaped downstream hook with a vertical portion extending radially from the duct wall and a horizontal portion housed in a holding hook positioned at the top of a tooth of the disc, and an upstream hook extending substantially radially from an upstream area of the duct wall and held axially between the flange and the disc.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 17/18 - Final actuators arranged in stator parts varying effective number of nozzles or guide conduits

Abstract

A turbine ring assembly provided with a CMC-sectored turbine ring and a ring support structure, each sector of the ring containing a base from which an upstream hooking lug and a downstream hooking lug axially spaced from each other extend radially outwards, the support structure including an upstream radial clamp and a downstream radial clamp between which the hooking lugs of each sector are held, and the assembly including, for each sector, at least one pin and at least one passage passing axially through a hooking lug over an axial length of the passage. At least one pin containing a planar bearing surface facing an inner surface of the passage through which the pin passes, the bearing surface facing the inner surface extending axially over a length smaller than the axial length of the passage.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

IPC Classes  ?

• B64D 27/40 - Arrangements for mounting power plants in aircraft

Abstract

The present invention relates to a method for manufacturing an annular casing (3) for a turbomachine, this casing comprising: - an envelope (5) extending around an axis (X) and made of a composite material; - a layer (4) made of abradable material extending at the inside of the envelope; and - support panels (6) extending around the axis (X) and interposed between the envelope and the abradable layer, the method comprising the following steps: (a) fastening the support panels to the annular envelope; (b) preparing a paste by mixing a polymer resin and a fibrous reinforcement; (c) depositing the paste on an inner annular surface, for example of the support panels; and (d) curing the paste to form the casing, the method being characterized in that, in step (b), the paste further comprises a curing accelerator, for example based on an amine resin.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

One aspect of the invention relates to a cooling device (100) extending around an axis (X) and intended to cool a coaxial turbine casing for a turbomachine, the cooling device (100) comprising at least one cooling tube (120) extending circumferentially around the axis (X), the at least one tube (120) comprising a plurality of primary circulation orifices intended to cool the casing, the cooling device (100) being characterized in that the at least one tube (120) comprises a discharge orifice intended to discharge particles present in the at least one tube (120), the discharge orifice being located on a closure face closing the distal end (122) of the tube (120).

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components

Abstract

The invention relates to a method for impregnating a fibrous preform (110) comprising a three-dimensional weave, the method being characterised in that it comprises the following steps: - arranging a fibrous preform comprising a three-dimensional weave in the moulding cavity of a mould (100); - arranging a powder (121, 122) made of thermoplastic material having a particle size of between 1.0 µm and 2000 µm in the moulding cavity of the mould; - a step of compressing the elements present in the moulding cavity of the mould, in order to allow the powder made of thermoplastic material to impregnate the fibrous preform; and - a step of heating to a temperature greater than or equal to the glass transition temperature of the thermoplastic material.

IPC Classes  ?

• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

The invention relates to an assembly (201) comprising a turbine engine (203) of an aircraft (200) and a mounting pylon (205) for the turbine engine. The assembly (201) comprises a first suspension member (217) connected to an upstream structural casing (209), a second suspension member (219) connected to an intermediate structural casing (211), and a third suspension member (221) connected to a downstream structural casing (215). The third suspension member (221) comprises a cavity (223), which is secured to the pylon (205) on its internal part (205a) and comprises an opening (223a) in an internal surface (223b), a block of material (225), which is accommodated in the cavity (223), and a coupling device (227) which is inserted into the cavity (223) at the opening (223a) and passes through the block of material (225). The coupling device (227) has a plate (227a) bearing on an external surface (225a) of the block of material (225) such that, when the block of material (225) expands, the block of material (225) exerts a pressure force on the plate (227a), thereby causing a radial movement of the coupling device (227).

IPC Classes  ?

• B64D 27/40 - Arrangements for mounting power plants in aircraft
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings

Abstract

The invention relates to an assembly (201) comprising a turbine engine (203) of an aircraft (200) and a mounting pylon (205) for the turbine engine (203). The assembly (201) comprises a first suspension member (217) connected to an upstream structural casing (209), a second suspension member (219) connected to an intermediate structural casing (211), and a third suspension member (221) connected to a downstream structural casing (215). The third suspension member (221) comprises a coupling device (223) that extends radially from the downstream structural casing (215) and is connected to a pivot (225) of a sliding pivot connection (227), the sliding pivot connection (227) also comprising a connection pin (A) that is fastened to the pylon (205) and forms an acute angle (θ) with the axis (X) such that a modification of the axial position of the coupling device (223) brings about a modification of the radial position of the coupling device (223), as a result of the pivot (225) sliding along the connection pin (A).

IPC Classes  ?

• B64D 27/40 - Arrangements for mounting power plants in aircraft
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings

Abstract

The present disclosure relates to a sealing assembly for a turbine engine, the assembly comprising a stator part (1), a rotor part (2), an axial seal (3) that provides sealing between an outer cavity (4) and an inner cavity (5) and comprises an inner platform (32) suitable for sliding on a downstream axial end (11) of the stator part (1) as well as a radial face (31) mounted axially opposite an upstream face (21) of the rotor part (2), the sealing assembly further comprising at least two fins (7) situated between the radial face (31) and the upstream face (21), an additional fin (8), an outer platform (33) designed to extend opposite the additional fin (8), and an injection duct (35) passing through the radial face (31) of the axial seal (3) and opening radially between the two fins (7).

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F16J 15/44 - Free-space packings
• F16J 15/447 - Labyrinth packings

Abstract

The present disclosure relates to a propulsion assembly (1) comprising: - a main channel (9) which extends between an air inlet (91) and a splitter (92) that divides the main channel (9) into a primary flow path (10) and a cooling flow path (20), - an ejection duct (30) which extends between an ejection inlet (31) that opens into the primary flow path (10) and an ejection outlet (32), and - a discharge valve (40) which is configured to discharge an air flow into the ejection duct (30), the ejection duct (30) being arranged between the cooling flow path (20) and the primary flow path (10) such that the ejection outlet (32) opens out radially outside the external casing of the propulsion assembly (1), the ejection outlet (32) being located downstream of the cooling outlet (22).

IPC Classes  ?

• F02C 3/13 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
• F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows

Abstract

An aeronautical propulsion system includes a ducted fan section with a fan shaft extending along a longitudinal axis, supported by a first guiding system. A drive shaft to be driven by a turbine and that is supported by a second guiding system includes thrust bearings. A reduction structure, including an epicyclic gear train with a ring gear, couples the drive shaft to the fan shaft such that the drive shaft rotates at a higher speed than the fan shaft. A support attaches the reduction structure to a stator. A coupling device connects the drive shaft to the reduction structure and compensates for misalignment therebetween. The coupling device includes shaft sections and radial flexibility elements connecting the shaft sections. Specific dimensional ratios between axial distances of the guiding systems, reduction structure, support, and coupling device elements relative to a reference plane are defined to optimize system performance.

IPC Classes  ?

• H10W 72/00 -

Abstract

The invention relates to a device for removably attaching a piece of equipment (E), comprising a base (200) and a frame (100) to which the piece of equipment is rigidly connected; the frame (100) having a first side (101) and a second side (102), opposite each other with respect to a first axis (A1) of the frame (100), and a base plate (103) extending between the sides (101, 102) in parallel with the first axis (A1) in order to rest on an upper surface (203) of the base (200). The device comprises at least a first abutment (104) arranged on the frame (100) in order to be engaged under a hook (204) rigidly connected to the base (200), and a second abutment (106) arranged on the frame (100) in order to engage with a tie rod (206) connected to the base (200).

IPC Classes  ?

• F16M 11/04 - Means for attachment of apparatusMeans allowing adjustment of the apparatus relatively to the stand
• F16B 1/00 - Devices for securing together, or preventing relative movement between, constructional elements or machine parts
• F16M 11/22 - Undercarriages with or without wheels with approximately constant height, e.g. with constant length of column or of legs
• G01P 1/00 - Details of instruments

Abstract

The invention relates to an assembly for a turbine engine having a longitudinal axis X, the assembly being configured to be arranged between a lubrication chamber of a speed reducer and a lubricant-tight zone, the assembly comprising: a casing arm configured to be provided in an air circulation duct intended to at least partially supply a gas generator of the turbine engine, the casing arm being formed by a wall delimiting a hollow interior space configured to be passed through by a cable, the hollow interior space being closed radially towards the interior by a lubricant-tight bottom partition, the bottom partition having a cable passage opening; a ring dimensioned so as to sealingly surround a portion of the cable, the ring being housed in the cable passage opening and being fastened to the bottom partition, the ring comprising a main body having a shape substantially complementary to the opening; sealing means provided at a junction interface between the ring and the opening.

IPC Classes  ?

• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 25/18 - Lubricating arrangements

Abstract

The invention relates to a clip (30) for retaining a harness (24) for an aircraft engine testing machine (10), the clip (30) being formed as a single piece with two lateral legs (32, 34) connected by a bridge (36) extending between the legs (32, 34), a first of the lateral legs (32) comprising two branches (38, 40) which extend along an axis (A) perpendicular to the bridge (36) and which define between them a space (42) through which a harness (24) can pass, the branches (38, 40) having first axial ends (38a, 40a) connected together and to the bridge (36) and second axial ends (38b, 40b) which are opposite the first axial ends (38a, 40a) and which define a narrowed section (44) of said space (42).

IPC Classes  ?

• F16B 2/22 - Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material

Abstract

The invention relates to a detection device (4) for detecting the presence of an electrical arc on an electrical line (3) of an electrical circuit of an aeronautical system, comprising at least: - a measurement module adapted to obtain measurements of at least one current on said electrical line (3) and of an electrical voltage relative to said electrical line; - a computation module adapted to extract descriptors from said measurements; and the detection of the presence of an electrical arc, by applying a decision function, previously provided by a learning device (4'), to said descriptors.

IPC Classes  ?

• G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
• G01R 31/12 - Testing dielectric strength or breakdown voltage

Abstract

The invention relates to a rotor blade (20) for an aircraft turbine engine, this blade (20) comprising a blade airfoil (22) and a root (24) connected to the blade airfoil (22) by a platform (26), the blade airfoil (22) extending from the platform (26) to a free end (22a) comprising a recessed pocket (36), the blade airfoil (22) having a leading edge (28) and a trailing edge (30), and pressure-side and suction-side faces (32, 34) which extend from the leading edge (28) to the trailing edge (30), the blade (20) also having an internal circuit (38) for the passage of ventilation air, the internal circuit (38) extending from the root (24) to the free end (22a), the internal circuit (38) comprising an internal cavity (50) which is located at the free end (22a), just below the pocket (36), and which is connected to the bottom (44) of the pocket (36) by outlet openings (42), this cavity (50) having an elongate shape from the leading edge (28) to the trailing edge (30) and being surrounded by parts of the pressure-side and suction-side faces (32, 34).

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

The invention relates to a system for adjusting the pitch and de-icing the blades (14) of a propeller (12) of an aircraft, the system comprising a rotary drive element (20); a gear reduction device (24); first and second inverter devices (40) configured to be connected to an electrical power source delivering a DC voltage; a first low-radius rotary transformer (34) connected to the first inverter device (40) and delivering a first secondary AC voltage (VsAC1) for powering an electric motor (80) for adjusting the pitch of the blades of the propeller; a second low-radius rotary transformer (50) connected to the second inverter device (56) and delivering a second secondary AC voltage (VsAC2); a de-icing device (60) carried by the rotary drive element and powered by the second secondary AC voltage; and a regulation unit configured to maintain the DC voltage delivered by the electrical power source at a constant value.

IPC Classes  ?

• B64C 11/44 - Blade pitch-changing mechanisms electric
• B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating

Abstract

Turbomachine (1) comprising a cylindrical exhaust case (8) having an axis (AX) extending along an axial direction (X) and defining an exhaust volume (Ve) through which an exhaust flow (Fe) circulates. An exhaust case arm (20) connects a frame (10) to the exhaust case (8). This exhaust case arm (20) comprises a fairing (22) which delimits an internal volume (V20) and which comprises an intake port (26) for a cooling airflow (FR) and an outlet port (52, 62) connecting the internal volume (V20) to the exhaust volume (Ve). A flow management device (70) is arranged to allow the flow of the cooling flow (FR) and to oppose a reversed flow (Finv).

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/30 - Exhaust heads, chambers, or the like

Abstract

The invention relates to a method for estimating a state of health of an aircraft engine, comprising a training phase during which an agent is trained by reinforcement to estimate hyperparameters for a Bayesian estimator, and a deployment phase during which the Bayesian estimator estimates a state of health of the aircraft engine using hyperparameters provided by the agent.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring
• G06N 7/01 - Probabilistic graphical models, e.g. probabilistic networks
• G06N 3/006 - Artificial life, i.e. computing arrangements simulating life based on simulated virtual individual or collective life forms, e.g. social simulations or particle swarm optimisation [PSO]
• G06N 3/08 - Learning methods
• G06N 20/00 - Machine learning

Abstract

A method for controlling the speed of an engine assembly of an aircraft, including updating the speed setpoint of the engine assembly as a function of the current state-of-charge of an onboard energy storage device, and controlling the engine assembly according to the speed setpoint of the engine assembly, as well as a control device suitable for implementing this method and an engine assembly and an aircraft incorporating such a control device.

IPC Classes  ?

• B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
• B64D 27/33 - Hybrid electric aircraft
• B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries

Abstract

An aeronautical propulsion system includes a stator, an unducted fan section with a fan shaft extending along a longitudinal axis, and a first guiding system supporting and rotationally guiding the fan shaft. A drive shaft extends along the longitudinal axis and is driven by a turbine. A second guiding system supports and rotationally guides the drive shaft. A reduction structure couples the drive shaft to the fan shaft such that rotation of the drive shaft at a first speed drives rotation of the fan shaft at a second speed less than the first speed. A coupling device connects the drive shaft to the reduction structure and compensates for misalignment therebetween. The coupling device includes shaft sections and radial flexibility elements connecting the shaft sections. A ratio of a difference between axial distances of the radial flexibility elements from a reference plane to one of the axial distances is between 0.55 and 2.0.

IPC Classes  ?

• B64D 27/40 - Arrangements for mounting power plants in aircraft

Abstract

A vaned impeller for aircraft turbomachine, comprising several vanes with a heel circumferentially extending on either side of the blade tip respectively into a first heel portion, and a second heel portion. Between adjacent first vane and second vane of the impeller, the latter comprises a member for reconstituting a gas circulation path, arranged in a first recess provided on the radially inner surface of the first heel portion of the first vane, and in a second recess provided on the radially inner surface of the second heel portion of the second vane, the first and second recesses each having a bottom surface for cooperating by friction with a radially outer friction surface of the member.

IPC Classes  ?

• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

The invention relates to a device (300) for measuring parameters of an aerodynamic flow in a duct of a turbomachine, the device comprising: - a guide housing (200) defining an inner cavity (230), - a comb (100) comprising a comb body (120) which extends between a comb head (110) and a lower end (123) of the comb (100), the comb head (110) being slidably mounted in the inner cavity (230), the comb body (120) extending outside the guide housing (200) through the opening present in the lower part (220) of the guide housing (200), at least one spring element (130) interposed between the comb head (110) and the upper part (210) of the guide housing (200), the comb head (110) being movable in the inner cavity (230) between a first position and a second position, the comb body further comprising means (121) for measuring parameters of an aerodynamic flow.

IPC Classes  ?

• G01M 9/06 - Measuring arrangements specially adapted for aerodynamic testing
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

The invention relates to a tooling (1) for localized heat treatment of a metal component comprising a weld bead that is to be relieved of stress. The tooling comprises a clamp (2) which has a stationary jaw (4), a movable jaw (5) which can move toward or away from the stationary jaw, and an assembly (6) for guiding this movement. The stationary jaw and the movable jaw each have a shoe (15) and a clamping element (19). The two shoes are mounted facing each other and can be moved toward or away from each other, by means of their respective clamping element which pushes them toward each other when it is actuated. Each of the shoes is equipped with an abutment plate (25) and a heating element that heats the abutment plate, the two abutment plates being arranged facing each other.

IPC Classes  ?

• C21D 1/26 - Methods of annealing
• C21D 1/40 - Direct resistance heating
• C21D 8/00 - Modifying the physical properties by deformation combined with, or followed by, heat treatment
• C21D 9/50 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for welded joints

Abstract

The invention relates to a method and an electronic control unit for controlling a set of rotodynamic pumps (1,2,3) arranged in series. This set comprises at least one upstream rotodynamic pump arranged directly upstream of a downstream rotodynamic pump. According to this method, a rotational speed of the upstream rotodynamic pump and a degree of opening of a regulating valve of the upstream rotodynamic pump are controlled as a function of a saturation margin of the downstream rotodynamic pump and of a flow rate coefficient of the upstream rotodynamic pump. The saturation margin of the downstream rotodynamic pump is a difference between the current pressure and the saturation pressure of the liquid at the inlet of the downstream rotodynamic pump. The flow rate coefficient of the upstream rotodynamic pump is the volumetric flow rate of the upstream rotodynamic pump divided by the rotational speed of the upstream rotodynamic pump.

IPC Classes  ?

• F04D 15/00 - Control, e.g. regulation, of pumps, pumping installations, or systems
• F02K 9/46 - Feeding propellants using pumps
• F02C 7/236 - Fuel delivery systems comprising two or more pumps
• F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed

Abstract

A method for controlling the speed of an engine assembly of an aircraft. The engine assembly includes at least a combustion engine and an electric machine mechanically coupled to the combustion engine and electrically connected to an onboard energy storage device of the aircraft. The method includes steps of comparing an electrical reserve required for engine assistance with an available electrical reserve, and controlling the speed of the engine assembly as a function of the difference between the electrical power reserve required for engine assistance and the available electrical power. A control device suitable for implementing this method, as well as the engine assembly and aircraft incorporating the control device.

IPC Classes  ?

• B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
• B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
• B64D 31/06 - Initiating means actuated automatically

Abstract

A system for exchanging power in an aircraft, the system including a voltage bus; a low-pressure electromechanical converter; a high-pressure electromechanical converter; and for each electromechanical converter a voltage control module and a control module for ensuring that the exchange setpoint is observed. The system further includes a power adjustment module configured, for at least one of the electromechanical converters: to determine a voltage correction; and to apply, in the voltage control module associated with the relevant electromechanical converter, the voltage correction to a voltage setpoint so that the voltage control module adjusts the bus voltage to the corrected voltage setpoint.

IPC Classes  ?

• H02J 1/102 -
• B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants

Abstract

A device for setting the pitch of a vane for a turbomachine, the device including a vane that is pivotable in a first direction and includes a leading edge, a trailing edge and a base which has an opening; a fin that includes a leading edge, a trailing edge and a portion accommodated in the opening; a controller that rotates the vane and moves the portion of the fin; so as to keep a variation in a C/D ratio below 10%, the ratio being between a projection in a direction of projection normal to the first direction of a: length C between the leading edge and the leading edge of the fin; and length D between the leading edge and the trailing edge of the vane.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type

Abstract

In a method for navigating a vehicle provided with a LiDAR and an inertial measurement unit, both connected to an electronic navigation unit that implements a first simultaneous localization and mapping algorithm and a second data merging algorithm, the first algorithm receiving, as an input, first location data from the LiDAR in order to calculate a first displacement from an initialisation position, the second algorithm receiving, as an input, the first displacement and second location data from the inertial measurement unit and outputting a merged second position of the vehicle, the second algorithm implements invariant extended Kalman filtering and in that the merged second position is introduced into a feedback loop which feeds into the first algorithm as an input in order to calculate a new position, which becomes the initialisation position.

IPC Classes  ?

• G01S 17/931 - Lidar systems, specially adapted for specific applications for anti-collision purposes of land vehicles
• B64U 20/80 - Arrangement of on-board electronics, e.g. avionics systems or wiring
• G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
• G01S 17/933 - Lidar systems, specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
• G05D 1/242 - Means based on the reflection of waves generated by the vehicle
• G05D 1/245 - Arrangements for determining position or orientation using dead reckoning
• G05D 109/20 - Aircraft, e.g. drones

Abstract

The invention relates to an inner shroud sector (1) configured to internally delimit a secondary duct (41) of an aircraft turbomachine (50), the inner shroud sector (1) comprising a downstream end (2) which comprises an upstream longitudinal portion (3) and a downstream longitudinal portion (4) which are connected by a middle portion (5) and are configured to extend, respectively, in an upstream extension and internally to a nacelle inner casing (31), the inner shroud sector (1) comprising an inner layer and an outer layer of composite material, the middle portion (5) of the downstream end (2) comprising at last one volume of intumescent material sandwiched between the inner layer and the outer layer of the composite material so as to form a local thickened portion in the longitudinal direction.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A method for adjusting a turbine engine part to be placed in a gas flow path of the turbine engine, the part having previously undergone an operation of adding material to fill a defect in at least one zone of its surface, resulting in an excess thickness in the at least one zone of its surface, including the steps of controlling formation of a three-dimensional image of the part, identifying the at least one zone of the part surface including the excess thickness, and identifying the excess thickness, in the three-dimensional image of the part, determining a trajectory of an adjustment tool, according to the geometry of the identified excess thickness, and controlling adjustment of the part according to the determined trajectory.

IPC Classes  ?

• B23P 6/00 - Restoring or reconditioning objects
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

An aircraft turbomachine comprising at least one propulsion shaft, an electric machine (1) connected to the propulsion shaft by a transmission line, a control device (3) comprising a correction module (4) configured to determine a correction torque (TRQcorr) to correct a torsion mode of the transmission line and a regulation module (5) configured to determine a setpoint torque (TRQcons) from a setpoint distribution voltage (Vdc_cons), a measured distribution voltage (Vdc_mes) and an angular velocity (W) of the electric machine (1) so as to ensure the quality of the electrical network (6).

IPC Classes  ?

• H02P 21/05 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation specially adapted for damping motor oscillations, e.g. for reducing hunting
• H02P 29/50 - Reduction of harmonics
• H02P 23/04 - Arrangements or methods for the control of AC motors characterised by a control method other than vector control specially adapted for damping motor oscillations, e.g. for reducing hunting

Abstract

This nozzle (36, 36a) for a turbine comprises an inner ring (40) and a bladed ring (42) provided with a plurality of blades (46), with an inner platform (48) and with a flange (50) extending radially inwards from the inner platform (48), the inner ring (40) being provided with a platform (52), with an upstream flange (56) and with a downstream flange (58), the upstream and downstream flanges (56, 58) extending radially outwards from the platform (52) of the inner ring (40) while being attached to the flange (50) of the bladed ring (42), the inner ring (40) comprising at least one collar (62) extending at least radially outwards from the platform (52) of the inner ring (40) while remaining at a distance from the upstream and downstream flanges (56, 58), a plurality of orifices (64) being formed in the collar (62).

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

EL1111010) of the core (10).

IPC Classes  ?

• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B64C 11/26 - Fabricated blades
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]

Abstract

LTT).

IPC Classes  ?

• F01D 5/16 - Form or construction for counteracting blade vibration
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

The invention relates to a blade (10) comprising a blade core (20) forming a blade root, a shank and an airfoil body portion (13), the blade core being made of composite material comprising a fibrous reinforcement having a three-dimensional weave between a first plurality of warp yarns and a first plurality of weft yarns oriented respectively in the longitudinal direction and in the transverse direction. The blade (10) further comprises skins (30, 31) made of composite material comprising a fibrous reinforcement having a three-dimensional weave between a second plurality of warp yarns oriented mainly in a first direction (D1) forming an angle with the longitudinal direction (DL) of between ± 10° and ± 80° and a second plurality of weft yarns oriented mainly in a second direction (D2) forming an angle with the transverse direction (DT) of between ± 10° and ± 80°.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• D03D 25/00 - Woven fabrics not otherwise provided for

Abstract

One aspect of the invention relates to a fastening collar (8) for fastening a cooling tube (2) of a cooling system of a turbine engine casing, the fastening collar (8) comprising a main body (10) having: - a circular portion (16) configured to surround the cooling tube over at least part of its circumference, and - two planar portions (19, 20) extending in the same plane (L, T), each arranged at one end of the circular portion. The fastening collar comprises a retaining ring (40) made of a graphite material and inserted into the main body, and a means for preventing the retaining ring from moving longitudinally in the main body. A second aspect of the invention relates to an assembly (4) for fastening a cooling tube, the assembly (4) comprising a fastening support (6) secured to the turbine engine casing, a fastening collar according to the invention, and a clamping device (60) for clamping the collar to the support.

IPC Classes  ?

• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

Abstract

The invention relates to a method for manufacturing a turbine engine part, which comprises: - producing a fibrous blank (100) of a structure with an aerodynamic profile by three-dimensional weaving of yarns, the blank comprising an internal housing (106), - inserting a shaping piece (400) into the internal housing (106) of the fibrous blank so as to form a preform, - densifying the fibrous preform with a matrix. The shaping piece (400) consists of a plurality of unit blocks (401-411) introduced one after another into the internal housing (106).

IPC Classes  ?

• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

The invention relates to a method for manufacturing a blade or a propeller, the method comprising: - producing a fibrous blank (100) of a structure with an aerodynamic profile by three-dimensional weaving of yarns, the blank comprising an internal housing (106), - inserting a shaping piece (400) into the internal housing (104a) of the fibrous blank so as to form a preform, - densifying the fibrous preform with a matrix. The foam shaping piece (400) extends in the longitudinal direction in the aerodynamic profile portion over a height (H400) of between 20% and 80% of the height (H110) of the aerodynamic profile portion. The foam shaping piece further comprises recesses (410, 420a, 420b) each provided on at least one of the first or second outer faces (400a, 400b) of the foam shaping piece (400), the one or more recesses being filled with a material having a higher density than that of the foam of the shaping piece.

IPC Classes  ?

• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

The invention relates to a method for controlling an accelerometric sensor, the accelerometric sensor having electrodes forming capacitors of variable capacitance depending on a distance between the electrodes, a control unit being arranged to carry out a capacitance measurement operation and a control operation which selectively comprises: a fine control phase in which a first voltage is applied between one of the fixed electrodes and the movable electrode, the other of the fixed electrodes being at the same potential as the movable electrode; and an extended control phase in which a second voltage is applied between one of the fixed electrodes and the movable electrode, the other of the fixed electrodes being at the same potential as the movable electrode and the second voltage being greater in absolute value than the first voltage. The control unit is arranged to implement self-calibration. The invention also relates to a method using such a sensor.

IPC Classes  ?

• G01P 21/00 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass
• G01P 15/13 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration by making use of inertia forces with conversion into electric or magnetic values by measuring the force required to restore a proofmass subjected to inertial forces to a null position
• G01P 15/125 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration by making use of inertia forces with conversion into electric or magnetic values by capacitive pick-up

Abstract

The invention relates to a method (100) for assembling an electronic component (1) on a substrate (2), the method comprising the following steps - depositing a sintering material (7) on one face of a substrate (2), so as to form at least three columns of the sintering material; - stacking the electronic component (1) on the columns by means of a gripping tool (22) designed to place the electronic component on the columns at a predetermined height (h) from the face of the substrate (2); - heating the stack formed at least by the substrate (2), the columns and the electronic component (1) in order to sinter the columns, the at least three columns solidifying to form at least three sintered studs, the bond line thickness of which is related to the predetermined height (h).

IPC Classes  ?

• B81C 3/00 - Assembling of devices or systems from individually processed components

Abstract

This method (200) for producing a composite spacer ring for a turbine engine fan comprises preparing (210) an upstream skin preform, preparing (220) a downstream skin preform, preparing (230) an insert preform, inserting (251) the insert preform between the upstream skin preform and the downstream skin preform so as to form a rotating spacer ring preform, and baking (260) the rotating spacer ring preform. The preparation (210) of the upstream skin preform and/or the preparation (220) of the downstream skin preform comprises drape forming (212, 222) prepreg tows on a skin mold by means of automated fiber placement.

IPC Classes  ?

• B29C 70/70 - Completely encapsulating inserts
• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29L 31/26 - Sealing devices, e.g. packaging for pistons or pipe joints
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A system for exchanging power in an aircraft includes voltage bus, a low-pressure and high-pressure electromechanical converters, and for each electromechanical converter, a voltage control module. The system further includes a computer providing a sharing setpoint between the exchanged powers, the sharing setpoint varying over time; and for at least one of the electromechanical converters: a module that ensures the sharing setpoint is observed. The module is configured to adjust the power that is exchanged by the relevant electromechanical converter in order to observe the received sharing setpoint, taking into account a received evaluation of the power exchanged by the other of the electromechanical converters.

IPC Classes  ?

• B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
• B64D 27/33 - Hybrid electric aircraft
• B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
• B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
• H02J 1/10 - Parallel operation of dc sources
• H02J 1/102 -

Abstract

A system for measuring a clearance between a rotating blade and a casing of a turbomachine includes a removable fastening device provided with a locking mechanism to maintain the mounted position of the measurement system on the casing, a retractable stop mechanism provided with a guide and a finger that hold the rotating blade in a measurement position, a remote acquisition device that measures at least one clearance between the rotating blade and the casing when the removable fastening device is in the mounted position and the retractable stop mechanism is in the deployed position, and a plate to which the removable fastening device, the retractable stop mechanism and the remote acquisition device are attached.

IPC Classes  ?

• G01B 11/14 - Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures

Abstract

A fan section of a propulsion system includes a fan rotor including twenty-two blades and having a solidity greater than or equal to 0.9 and less than or equal to 1.3, where the solidity is equal to a ratio between a chord at the tip of a blade and an inter-blade pitch at the tip of the blade. The fan section has a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the tip of the blade greater than or equal to 270 m/s and less than or equal to 380 m/s. The pressure ratio and the peripheral speed are measured at cruising power.

IPC Classes  ?

• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan