The invention relates to a guide vane for attachment to a stator shroud of a gas turbine engine, comprising:—a profiled part intended to extend in a gas flow in order to guide the gas flow, the profiled part having a pressure-side surface and a suction-side surface, and—a platform having a guide surface from which the profiled part extends, a first lateral surface and a second lateral surface, the second lateral surface being able to be arranged facing a first lateral surface of an identical adjacent guide vane, fanning a raised portion which prevents a parasitic transverse flow of the gas flow, while creating a depression which at least partially compensates for the obstruction of the gas flow by the raised portion.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventor
Cavarroc, Marjorie Christine
Peigney, Erwan
Aymonier, Cyril
Aubert, Guillaume
Poulon, Angélique Nadine Jeanne
Abstract
A method for depositing on a metal substrate a continuous coating of aluminum oxide by induction heating-assisted pressurized, temperature-controlled chemical deposition, the method including a solvothermal synthesis procedure based on an aluminum oxide precursor dissolved in a water-co-solvent mixture heated by induction to a temperature of between 400° C. and 700° C. and a pressure of between 1 MPa and 25 MPa.
C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
3.
METHOD FOR SIMULATING THE FLOW OF A FLUID IN CONTACT WITH A MOVING SOLID
The invention relates to a method for simulating a fluid in contact with a moving solid modelled by a series of fixed positions (XA), the method comprising the steps of: —generating (E1) a fixed lattice (M1); —generating (E2) an auxiliary lattice (M2) of the solid (S) in a first position (XA) wherein each auxiliary lattice (N2) comprises a particle (P) comprising information on the volume (V2) of the auxiliary lattice (N2); —determining (E3) the position (XPA) of the particles (P) in the fixed lattice (M1); —calculating (E4, E5) the volume of the solid (V1s) and the volume fraction of the fluid (εF) in each fixed lattice (N1) based on the particles (P); —solving (E6) discretised Navier-Stokes equations using the finite volume approach applied to the volume fraction of the fluid (εF); —and, for each subsequent position (XB, XC) of the solid (S), a step (E7) of moving the particles (P) followed by the determining (E3), calculating (E4, E5) and solving (E6) steps.
G06F 30/28 - Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
A stator element an electrical conductor that is elongate and hollow in order to define a flow channel that allows a coolant to flow from one end of the conductor to the other. The stator element further includes a conductor designed to pass an electric current and a connection element located at one of the ends of the conductor. The connection element includes a fluid connection terminal designed to allow coolant to enter the channel or to exit from the channel, and an electrical connection terminal designed to electrically connect the conductor. The conductor and the connection element are formed of a single unitary part.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
A turbomachine assembly includes a high-pressure compressor driven by a high-pressure shaft, a low-pressure compressor driven by a low-pressure shaft, the low-pressure shaft being driven at a lower speed than the high-pressure shaft, a first power converter driven by the high-pressure shaft, an air circulation system including a first air bleed port positioned in the high-pressure compressor and a second air bleed port placed upstream of the first air bleed port, a device that determines an operating condition of the turbomachine assembly, and a controller that sends transfer instructions to the first power converter for transferring a power from the high-pressure shaft to the low-pressure shaft or a power from the low-pressure shaft to the high-pressure shaft depending on the operating condition.
A method for a turbomachine having a high-pressure shaft driving a high-pressure electric machine and from which a high-pressure power taken off and a low-pressure shaft driving a low-pressure electric machine and from which a low-pressure power is taken off, the generation mode corresponding to a predetermined sharing of power between the high-pressure power and the low-pressure power and the assistance mode corresponding to a request for injection of an additional power into the high-pressure shaft or the low-pressure shaft, a method in which, to reach the requested additional power, when the high- or low-pressure power takeoff is interrupted and the high- or low-pressure electric machine respectively driving the high- or low-pressure shaft whose takeoff is interrupted enters motor mode.
There is provided an assembly of annular sectors of an annular multi-element acoustic component, each sector including a plurality of rows of hollow complex acoustic elements each having a shape that steadily narrows between a base and a vertex, each sector including a plurality of first rows including the same number of hollow complex elements and one or more second rows including one less hollow complex element than the first rows, each second row further including a male attachment element on one of the assembly edges and a female attachment element on the other assembly edge, the female attachment element having the same dimension as a hollow complex element along the direction of assembly.
A method for forming an acoustic resonator panel for an aircraft propulsion assembly nacelle, the acoustic panel including cells with transverse internal obstacles in order to lengthen the path traveled by the sound waves. The method includes forming a perforated metal sheet, stacking a plurality of thermoplastic cellular cores and at least one perforated sheet, two successive cellular cores being separated by a perforated sheet, compacting the stack, and thermoplastic welding.
B29C 65/36 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
B21D 53/92 - Making other particular articles other parts for aircraft
B29C 65/00 - Joining of preformed partsApparatus therefor
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 15/18 - Layered products essentially comprising metal comprising iron or steel
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
9.
VARIABLE LENGTH FIN HEAT EXCHANGER AND CORRESPONDING TURBOMACHINE
A heat exchanger for a turbomachine of an aircraft, the heat exchanger having a plurality of fins intended to be swept by a first fluid in a first direction, the fins extending in a second direction between a first panel and a second panel, being arranged in several rows in a third direction, and being arranged in a staggered manner, each row of fins being parallel and connected to one another. The heat exchanger can be annular, centered on the third direction and can have an inner cylindrical surface defining an inlet and an outer cylindrical surface defining an outlet, and the fins can have a length which decreases radially in the heat exchanger, in the first direction, between the inner cylindrical surface and the outer cylindrical surface.
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Casing of a gas turbine engine compressor comprising openings cut in the thickness of the casing from an inner surface of the casing and arranged side by side over a circumference of the casing, characterised in that it also comprises a movable ring, formed by at least two annular portions, positioned on an outer surface of the casing opposite the openings and able to move along the circumference of the casing such as to open and close the openings of the casing to activate or deactivate a casing treatment, the movable ring comprising the same number of slots as there are openings in the casing.
A method for manufacturing a propeller blade or vane made of composite material, includes making a single-piece fibrous blank by three-dimensional weaving between warp yarns and weft yarns, including an airfoil part and a root part including a non-interlinking, the root part including at least one changing sub-area in which the number of weft yarns crossing on either side of the non-interlinking increases gradually from the airfoil part to the free end of the root part, shaping the fibrous blank to obtain a fibrous preform, densifying the preform by a matrix to obtain a propeller blade or vane made of composite material.
A method and a device for classifying and localizing an object in an image sequence. The proposed method includes obtaining a sequence of one or more images captured by a camera; and determining, by a classifier-localizer module based on the obtained image sequence a class assigned to the object, the assigned class being selected from among a list of classes; and an estimated position of the object; the classifier-localizer module being configured based on reference image sequences to minimize a multi-objective loss function representative both of an objective of classification and an objective of object localization in the reference sequences.
This disclosure relates to an assembly for a gas turbine engine comprising:
a first rotary spool (222, 262, 282);
a second rotary spool (20, 220, 260, 280); and
an electrical system (4) comprising:
a bus (40);
a first generator (411);
a second generator (421);
a first converter (410);
a second converter (420); and
a control device (412, 422, 432, 4000).
A casting core includes a main portion made of molybdenum or a molybdenum alloy, and, at the surface of the main portion, at least two protuberances made of a refractory material, the whole of the main portion and the protuberances being covered with an anti-oxidation coating.
A fibrous preform of a core portion of a fibrous reinforcement for a composite material part, the preform having an elongate shape along a longitudinal direction and being formed by three-dimensional weaving of first yarns extending along the longitudinal direction with second yarns transverse to the first yarns, the preform including two longitudinal ends for articulation with other parts and a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a first volume ratio of first yarns to second yarns that is greater than one, and each longitudinal end having a second volume ratio of first yarns to second yarns that is less than the first ratio and closer to one than this first ratio.
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
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A system for monitoring an aircraft assembly, the system comprising: a plurality of lubrication fittings, each lubrication fitting comprising a passive radio frequency identification component; and a grease gun comprising an radio frequency identification reader and a processor, wherein the processor is configured to: transmit a first signal to cause the radio frequency identification reader to transmit a radio frequency, RF, signal to the passive radio frequency identification components in the lubrication fittings; receive a unique identifier from the passive radio frequency identification component in the lubrication fittings; and transmit a second signal comprising the unique identifier to a digital system.
A method for automatically monitoring a plurality of rotating parts of rotating machines on the basis of a target database including a plurality of time signals from a distribution generated from each rotating part and on the basis of a source database including a plurality of time signals from a distribution S different from the distribution T generated from a source rotating part of a source rotating machine and being associated with an operating class, the monitoring being carried out by an adaptive deep learning model making it possible to adapt the source distribution to the target distribution, the deep learning module being trained by minimization of a cost function relating to Gaussian kernel functions having a parameter σ; σ being calculated in each period on the basis of the difference in distributions weighted by a constant static value estimated on the basis of a Pascal's triangle.
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
18.
IMPROVED HEAT EXCHANGER DEVICE FOR AN AIRCRAFT TURBOMACHINE
A device including a heat exchanger body, an upstream hot-fluid header attached to the heat exchanger body and configured to collect a first fluid at a first temperature and to feed it to the heat exchanger body, an upstream cold-fluid header attached to the heat exchanger body and configured to collect a second fluid at a second temperature lower than the first temperature and to feed it to the heat exchanger body, at least the upstream hot-fluid header including a double wall forming a peripheral cavity surrounding a main cavity configured to receive a main flow of the first fluid, the peripheral cavity being configured to receive a secondary flow of the first fluid or of the second fluid.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE (France)
UNIVERSITE PAUL SABATIER - TOULOUSE II (France)
Inventor
Azzopardi, Stéphane Joseph
Le, Thanh Long
Richardeau, Frédéric
Jouha, Wadia
Barazi, Yazan
Rouger, Nicolas
Blaquiere, Jean-Marc
Vinnac, Sébastien
Picot, Mathis
Abstract
A device for controlling and protecting a power transistor, comprising: a nominal switching circuit for the transistor, a short-circuit detection circuit which keeps the transistor in the conducting state and detects an increase or decrease in the voltage VGS of the transistor relative to reference voltages representative of a short-circuit of the transistor; a protection circuit which discharges the gate of the transistor after the detection of a short-circuit; and a circuit for measuring and controlling the nominal switching circuit, the short-circuit detection circuit and the protection circuit.
H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit
G01R 31/26 - Testing of individual semiconductor devices
H03K 17/18 - Modifications for indicating state of switch
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventor
Riera, William Henri Joseph
Mondin, Gabriel Jacques Victor
Ottavy, Xavier Jean-Pierre
Abstract
The invention relates to a stator part (20) of a turbine engine, comprising a platform (22), a blade (24, 26) extending radially relative to a central axis (A), and a fin (28) extending radially from a fin root (44) to a fin tip (46), the fin comprising a lower side (48) and an upper side (50), each point (100) of the lower side or of the upper side defining a radial axis (Ar) passing through the point, each plane (Pr) that includes the radial axis defining a section (S) of the lower side or of the upper side, an angle defined in the plane between the root profile and a tangent to the section at an intersection (104) of the section and of the root profile being less than or equal to 45 degrees, the section being located between the root profile and the tangent.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventor
Riera, William Henri Joseph
Mondin, Gabriel Jacques Victor
Ottavy, Xavier Jean-Pierre
Abstract
The invention relates to a stator part (20) comprising a platform (22), a first blade (24), a second blade (26), and a fin (28) having a leading edge (30) and a trailing edge (32), the fin extending opposite an upper surface (124) of the first blade and a lower surface (126) of the second blade, the leading edge comprising a leading point (34) located on the platform, a tangent to the leading edge at the leading point extending between the first blade and a radial leading plane (Pa) and the leading point, and the trailing edge comprising a trailing point (36) located on the platform, a tangent to the trailing edge at the trailing point extending between the second blade and a radial trailing plane (Pf) and the trailing point.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
SAFRAN (France)
ECOLE NORMALE SUPERIEURE PARIS-SACLAY (France)
Inventor
Fragnaud, Cédric
Remacha, Clément
Roux, Stéphane
Betancur, Julian
Abstract
The invention relates to a non-destructive inspection method based on 3D modelling of a part, comprising: using an x-ray device to acquire images of the part at various projection angles; computing projections based on the images acquired at the various projection angles; in each of multiple iterations: generating simulated projections corresponding to the computed projections, based on a reference model of an external surface of the part and on a vector μ of transformation parameters of the reference model; modifying the vector μ with a view to reducing a discrepancy between the simulated projections and the computed projections; determining a corrected model of the external surface through transformation of the reference model by way of the vector μ resulting from the iterations; determining an effective model of the part by way of the corrected model.
G01N 23/04 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material
G01N 23/083 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and measuring the absorption the radiation being X-rays
A navigation assistance device intended to be embedded in a mobile system includes a monocular camera capable to simultaneously acquire a first image of a scene with a first depth of field and one or more second images of the scene with a second depth of field smaller than the first depth of field, a depth estimator that determines a depth map of the scene from the first image of the scene and the one or more second images of the scene, and a computer that calculates a navigation trajectory from the first image of the scene and the depth map of the scene.
A matrix for a heat exchanger to exchange heat between a first fluid and a second fluid, the first fluid being for instance air and the second fluid being for instance oil. The matrix comprises: a channel for the first fluid. an array of passages for the second fluid, the passages extending in the channel. The array supports at least two cooling fins. The matrix is made by a process of additive manufacturing. The fins are inclined with respect to each other along the direction of the flow of the first fluid. The array defines rectangular corridors for the first fluid.
F28F 1/12 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
F28D 7/16 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
F28F 1/34 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending obliquely
F28F 1/38 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and being staggered to form tortuous fluid passages
A turbojet includes in succession, from upstream to downstream in the flow direction of a primary air stream: a low-pressure casing, an intermediate casing, and a high-pressure casing that are longitudinally aligned and which jointly delimit an internal annular passage for the circulation of the air stream. The intermediate casing delimits a portion of the annular passage called a gooseneck and includes: an air discharge system able to extract air from the air stream circulating in a first zone of the gooseneck and to discharge it outside the passage, and an air extraction system able to extract air circulating in a second zone of the gooseneck for an air conditioning system, the second air extraction zone being located downstream of the first air extraction zone.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
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
26.
System for controlling the temperature of a heat transfer fluid in a circulation loop, and temperature control method
The invention relates to a system (1) for controlling the temperature of a heat transfer fluid (F) configured to transfer heat to a fluid to be heated (Q) originating from a cryogenic tank (R), the control system (1) comprising: a loop (2) for circulating the heat transfer fluid (F), comprising an engine branch (21) and a tank branch (22); a first engine heat exchanger (41), configured to heat the heat transfer fluid (F) to a second temperature (T2) above a maximum operating temperature (Tmax); a mechanical pump (3) configured to circulate the heat transfer fluid (F) in the circulation loop (2), such that, in a second engine heat exchanger (42), a first part of the heat is transferred from the heat transfer fluid (F) to the fluid to be heated (Q) and the heat transfer fluid (F) is cooled to a third temperature (T3) below the maximum operating temperature (Tmax), before it leaves the engine enclosure (EN-M).
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/224 - Heating fuel before feeding to the burner
27.
Fan blade or vane with cross-shaped or star-shaped composite root
A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including, along a span direction, a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile preform parts being connected to one another by three-dimensional weaving. The root includes a plurality of branches. The root preform part of the fiber preform includes a plurality of branches each extending in a branch of the root.
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 70/48 - 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]
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
28.
METHOD FOR INJECTING A HYDROGEN-AIR MIXTURE FOR A TURBINE ENGINE BURNER
An injection method, for an injection device in a combustion chamber of an aircraft turbine engine, said injection device comprising an internal channel surrounded by an external annular channel, said channels leading into said combustion chamber of the gas turbine, the method including injecting a gaseous hydrogen/air mixture having a greater hydrogen richness level than the stoichiometric amount into said internal channel and injecting air into the external annular channel so as to produce, at the outlet of the internal channel, a first flame front resulting from rich combustion surrounded by a second flame front resulting from lean combustion.
A method for detecting an anomaly in a system of an aircraft, including obtaining a current series of measurements of one or more physical quantities of the system, during a time period when the system is in operation; —on the basis of the current series of measurements, providing, by an encoder-decoder, a current reconstructed series; and —comparing the reconstructed current series with the current series of measurements in order to obtain a current series of anomalies. The method further includes computing a current distribution function of the current series of anomalies; —computing an area separating the current distribution function from a reference distribution function; and —comparing the area with a predefined threshold.
G06N 3/0442 - Recurrent networks, e.g. Hopfield networks characterised by memory or gating, e.g. long short-term memory [LSTM] or gated recurrent units [GRU]
The invention relates to a conditioning system (SC) for fuel (Q), which is configured to supply an aircraft turbine engine (M) with fuel (Q) from a cryogenic tank (R), the conditioning system (SC) comprising at least one first heat exchanger (31) configured to heat the flow of fuel (Q) to a circulation temperature (Te), at least one second heat exchanger (32) configured to heat the flow of fuel (Q) to an injection temperature (Ti), a distribution valve (4) configured to divide a direct fuel flow (Q1) and a recirculated fuel flow (Q2), configured to circulate in a recirculation branch (12) so as to reheat the main fuel flow (Qp) in the first heat exchanger (31) by means of the recirculated fuel flow (Q2).
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/236 - Fuel delivery systems comprising two or more pumps
31.
Method for manufacturing a composite material part intended to be articulated to other parts
A method for manufacturing a fiber preform for a part, includes weaving a first core texture of elongate shape extending in a longitudinal direction and comprising, in cross section, a central portion having, on its opposite sides, two edges each including two non-interlinked fibrous portions, shaping the first texture which involves at least opening out the non-interlinked portions to form a positioning surface defined by the portions thus opened out and by an interleaved portion, situated between these opened-out portions, which can be formed by a prolongation of the central portion, and positioning a second belt texture over the opened-out lateral portions and the interleaved fibrous portion, the second texture forming a loop around the shaped first texture to define empty spaces for articulation to other parts.
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 70/22 - 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
An aircraft landing gear assembly comprising: a ground contacting assembly (10); a main strut (8); a mounting bearing arranged for coupling the landing gear assembly to an aircraft such that the main strut supports the aircraft on the ground when the ground contacting assembly is in contact with the ground; a noise-inducing component; and a perforated sheet fairing (6a, 6b) comprising a body having a first surface and a second surface and plurality of holes (64) extending from the first surface to the second surface, each hole having an axis, wherein the perforated sheet fairing further comprises a plurality of airflow disruption elements (66) each extending towards the axis of a hole at an angle between 5° and 185° relative to the axis of the hole.
A method for monitoring a rotating machine in order to detect a fault in a bearing, the method including acquiring, from the rotating machine, a vibration signal measured by a vibration sensor; determining a first-order spectrogram by first-order cyclostationary analysis of the vibration signal using a delta transform and spectral standardisation; determining a second-order spectrogram by second-order cyclostationary analysis of the vibration signal using averaged cyclic coherence, a delta transform and spectral standardisation; and detecting a vibration signature of the fault in the bearing on the basis of the first-order spectrogram and the second-order spectrogram.
G06G 7/70 - Analogue computers for specific processes, systems, or devices, e.g. simulators for vehicles, e.g. to determine permissible loading of ships
A fibrous preform of a core portion of a fibrous reinforcement for a composite material part, the preform having an elongated shape along a longitudinal direction and being formed by first yarns extending along the longitudinal direction with second yarns transverse to the first yarns, the preform including two longitudinal ends intended for articulation with other parts and a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area including a stiffening segment including first non-woven yarns and each longitudinal end including a three-dimensional weave of the first yarns of this stiffening segment with second yarns.
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 70/48 - 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]
B29K 63/00 - Use of epoxy resins as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A Jacquard type loom intended to produce a fibrous structure by three-dimensional weaving between a plurality of warp yarns and a plurality of weft yarns extending in a horizontal direction, the loom including a reed movable between a rest position upstream of the rapier and a beat-up position of a fell of the fibrous structure in a beat-up direction parallel to the horizontal direction. The reed includes at least two stationary portions forming an angle therebetween. The reed is mounted on the loom by a positioning mechanism able to orient the reed about an axis of rotation so as to adjust an angular position of the stationary portions of the reed relative to a horizontal reference plane. The loom include vertical translation elements able to move the reed or the fell of the fibrous structure in the vertical direction.
D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
D03D 25/00 - Woven fabrics not otherwise provided for
D03D 41/00 - Looms not otherwise provided for, e.g. for weaving chenille yarnDetails peculiar to these looms
36.
Propeller blade or vane having a hollow composite root
A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.
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
A method for manufacturing a part made of composite material, includes the arrangement of a fibrous preform in a mould including an impregnation chamber, the impregnation chamber being closed by a membrane separating the impregnation chamber from a compaction chamber, the injection of an impregnation fluid into the impregnation chamber, and the injection of a compression fluid into the compaction chamber so as to apply a pressure on the membrane, the aspiration of the compression fluid present in the compaction chamber, the surface of the membrane present on the side of the compaction chamber including a plurality of grooves.
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]
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 70/54 - Component parts, details or accessoriesAuxiliary operations
An aircraft landing gear assembly comprising: a ground contacting assembly; a main strut; a mounting bearing arranged for coupling the landing gear assembly to an aircraft such that the main strut supports the aircraft on the ground when the ground contacting assembly is in contact with the ground; a noise-inducing component which, in use, with the landing gear assembly deployed, has a front region and a back region separated by a pair of side regions, such that flight motion of the aircraft causes airflow to encounter the front region followed by the side regions, followed by the back region; and a first flow deflector mounted adjacent to and spaced from a first side region, the first flow deflector having a leading edge and a trailing edge separated by first and second sides and being shaped with a curved profile between the leading edge and trailing edge that is curved towards the back region of the noise-inducing component so as to redirect airflow adjacent the first side region at an angle between 30 to 90 degrees relative to a free stream flow.
An aircraft landing gear system comprising: a plurality of sensors (26A-D) arranged to detect a known acoustic input signal (28) within one or more components of an aircraft landing gear structure (14); and a processor (52) configured to: receive data from the plurality of sensors (26A-D), the data corresponding to the detected known acoustic input signal (28); compare the data to a mapping function (74), wherein the mapping function (74) defines a relationship between a detected acoustic signal (28) and a known load on the one or more components of the aircraft landing gear structure (14); and estimate the load experienced by the one or more components of the aircraft landing gear structure (14) based on the data and the mapping function (74).
The invention relates to a method for producing a part made of a nickel-based alloy with a Y/Y′ microstructure in which at least one hot-forging step is performed, which method is characterised in that the temperature at which the part is heated in the forging step is maintained within a temperature range lower than the abnormal grain growth temperature range of the alloy, the hot-forging temperature being maintained at a temperature lower than the temperature of the part, the hot-forging temperature being such that the difference compared with the temperature at which the part is heated is less than 250° C. and preferably less than 150° C.
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
B21K 1/32 - Making machine elements wheelsMaking machine elements discs discs, e.g. disc wheels
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
41.
ROTATIONALLY SYMMETRICAL PART MADE OF COMPOSITE MATERIAL HAVING AN IMPROVED HOLDING CAPACITY
A method for manufacturing a composite material revolution part for a propulsion assembly includes making a fibrous preform on a mandrel having a profile corresponding to that of the part to be manufactured, and densifying the fibrous preform by a matrix. Making the fibrous preform includes forming a strip-shaped fibrous blank including at least one layer of continuous fibers and at least one layer of discontinuous fibers, the fibrous blank being shaped on the mandrel, the layer of continuous fibers of the fibrous blank extending at least over a complete turn around the mandrel.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/32 - 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 on a rotating mould, former or core
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
42.
METHOD AND SYSTEM FOR DETERMINING THE PRESSURE OF AN AIRCRAFT TIRE
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
SAFRAN (France)
SAFRAN ELECTRONICS & DEFENSE (France)
SAFRAN LANDING SYSTEMS (France)
Inventor
Neba, Eric Carin
Abstract
A method and a system for determining the temperature in a mounted aircraft tyre is characterized in that it has two temperature sensors installed inside the tire.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Appareils, instruments et équipements électriques et électroniques pour la navigation, le guidage, le téléguidage, le balisage, la localisation, le pilotage automatique, la stabilisation de véhicules aériens; systèmes de commande de vol pour aéronefs; calculateurs avioniques multifonctions; instruments et équipements de collecte de données pour l'aide à la maintenance (systèmes de gestion des données de vol); appareils, instruments et équipements d'analyse de données techniques et scientifiques (station d'analyses au sol); dispositifs de calculs pour les drones et les aéronefs; calculateurs de mission; simulateurs pour la direction et le contrôle des drones; appareils, instruments et équipements électroniques d'acquisition et de traitements de données et périphériques; supports d'enregistrement et de stockage électroniques pour le positionnement, le guidage et la transmission de données et de services par satellite; programmes d'ordinateurs enregistrés; logiciels pour l'exploitation et la commande de drones; logiciels de simulation et planification de vol; transmetteurs de signaux électroniques; émetteurs (télécommunication); composants électroniques, supports électroniques de banques de données de navigation et de positionnement, appareils d'analyse et de commande à distance mis à disposition sur des plateformes au sol pour l'exploitation de drones et d'aéronefs avec ou sans équipage; équipement d'essai en vol; appareils et instruments pour la télécommande et le guidage à distance de drones et autres aéronefs, à savoir les interfaces utilisateur de télécommande, les dispositifs de télémétrie de données, les émetteurs et récepteurs radio, les ordinateurs, les récepteurs du système de positionnement global et les instruments électroniques de navigation; batteries rechargeables pour drones; caméras et composants de caméras pour drones.
(2) Drones; drones de transport; véhicules aériens de transport de charge; transporteurs aériens par drones pour la manutention de charges; parties structurelles de drones. (1) Transport aérien de chargement; location de drones de livraison et de transport aérien de chargement; services de planification de vol; organisation et supervision de vols; services d'informations sur les vols et sur la navigation des drones et aéronefs avec ou sans équipage; fourniture de plans de vol; services de navigation par système de localisation mondial pour drones et aéronefs avec ou sans équipage; planification d'itinéraires pour drones et autres véhicules aériens [services de navigation]; navigation pour drones (positionnement et définition d'itinéraires et de trajectoires); services de remorquage de drones; consultation en matière de transport aérien de chargement; services de pilotage de drones; services d'assistance au pilote et au télépilote pour la compréhension et l'analyse du contexte et de la situation lors d'un vol de drone.
(2) Services d'assistance technique, à savoir fourniture de conseils techniques en matière de véhicules aériens sans pilote (UAV) ou drones; assistance technique pour véhicules aériens sans pilote (UAV) ou drones; personnalisation de matériel informatique et logiciels pour véhicules aériens sans pilote (UAV) ou drones, conception et développement de drones et systèmes de navigation pour drones; services scientifiques et technologiques ainsi que services de recherches mécaniques, aéronautiques et services d'analyses relatifs aux drones; services d'analyses de systèmes et de données informatiques et techniques provenant des drones; conception, élaboration, mise à jour (pour des tiers), installation, gestion et développement d'ordinateurs et de logiciels (programmes enregistrés) embarqués ou non et pour plateforme de contrôle de drones; tests, analyses et contrôles de signaux de navigation, de données et d'informations provenant des drones; services de simulations de vols; réalisation d'essais techniques et tests de vols, à savoir contrôle de qualité de drones; services d'ingénierie dronique et avionique; services de cartographie (géographie); logiciels en tant que service [SaaS] destinés aux drones et aéronefs avec ou sans équipage; mise à jour et maintenance de logiciels destinés aux drones et aéronefs avec ou sans équipage; plateforme informatique en tant que service [PaaS] destinée à la navigation des drones et des aéronefs avec ou sans équipage; analyse et gestion en matière de performance et de conformité (audit de qualité).
44.
REINFORCEMENT FOR A COMPOSITE BLADE OF A TURBOMACHINE, COMPRISING A MIXTURE OF FIBER CUTS AND A TACKIFIER
The present invention concerns a reinforcement for a blade of a turbomachine, the blade comprising a first outer skin and a second outer skin which are made of composite material each comprising an inner end portion spaced apart from each other in such a way as to delimit therebetween an inner cavity of the blade that opens into an opening at an inner end of the blade, the inner end being radially opposite the outer end, wherein the reinforcement is adapted to be arranged in the inner cavity in such a way as to close the opening, and wherein the reinforcement comprises a mixture of cuts of at least one fiber and a tackifier, the cuts having lengths comprised between 1 mm and 15 mm, the tackifier comprising an epoxy resin solubilized in a solvent.
Method for the manufacture of at least one skin, in particular of an acoustic panel for an aeronautical engine, including the laying of a thermoplastic material on a surface of a lay-up tooling, via a depositing tool configured to exert a pressure on the thermoplastic material and to heat the latter while it is being laid, wherein the lay-up tooling includes a thermal regulation device configured to locally heat the surface of the lay-up tooling.
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 35/04 - Heating or curing, e.g. crosslinking or vulcanising using liquids, gas or steam
B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation
B29C 70/34 - 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 and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 71/00 - Use of polyethers as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A method for monitoring the state of health of an aircraft turbomachine for a flight of interest VI, based on a setpoint vector XSC of input parameters relative to the turbomachine of interest in steady-state regime, the method using a database of values of input and output parameters in transient regime for a plurality of flights including the flight of interest, and values of input and output parameters in steady-state regime for a plurality of flights with the exception of the flight of interest. The transient data are used to estimate a transient prediction model f, at least one portion of the transient prediction model f then being used, associated with the steady-state data, in order to estimate a steady-state prediction model H of the turbomachine of interest for the flight of interest and to determine the behaviour, in steady-state regime, of the turbomachine for the flight of interest.
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner end portion (21, 31) spaced apart from each other in such a way as to delimit therebetween an inner cavity (4) of the blade (1) that opens into an opening (5), wherein the reinforcement (6) is adapted to be arranged in the inner cavity (4) in such a way as to close the opening (5), and wherein the reinforcement (6) comprises a stack of plies (61) that are superposed along a stacking direction (De) corresponding to a thickness direction (Pe) of the plies (61), at least two plies (61) having different lengths (Pl) and/or widths (PL) such that the reinforcement (6) has a profile of variable dimensions.
ONERA - OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventor
Rouffie, Anne-Laure
Franchet, Jean-Michel Patrick Maurice
Menou, Edern
Locq, Didier
Abstract
A nickel-based superalloy, includes, in percent by weight of the total composition Al 2.5-3.8, Co 7.9-16.9, Cr 9.7-13.1, Mo 2.6-4.1, Nb 0-0.41, Ta 0-1.9, Ti 4.4-6.4, W 1.9-4.2, B 0.010-0.030, C 0.010-0.040, Hf 0.20-0.40, Zr 0.040-0.070, the remainder being Ni together with inevitable impurities.
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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
49.
Electrical system for an aircraft equipped with a motor
An electrical system for an aircraft includes first and second buses, first and second electric generators, and first and second AC-to-DC converters. The first bus is connected to an AC network. The second bus is connected to a DC network of the aircraft. The first electric generator is connected to the first bus and a first rotary spool of an engine of the aircraft to exchange mechanical and/or electrical power. The first AC-to-DC converter is connected to the first and second buses. The second electric generator is connected to a second rotary spool of the engine of the aircraft. The second AC-to-DC converter connected to the second electric generator and to the second bus. One or more of the converters operates in a forced mode providing regulation of the electrical power of one or more buses, and/or a free mode providing regulation of a voltage of the second bus.
H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
H02P 101/25 - Special adaptation of control arrangements for generators for combustion engines
H02P 101/30 - Special adaptation of control arrangements for generators for aircraft
H02P 103/20 - Controlling arrangements characterised by the type of generator of the synchronous type
50.
DETECTING AN ELECTRIC ARC BY MEANS OF A BRAGG GRATING
An electrical distribution route for an aircraft includes electrical cables and electrical connection interface members, and a diagnostic and detection device for diagnosing and detecting an arc fault in the electrical distribution route. The diagnostic and detection device includes an optical fiber laid along the entire distribution route and having at least one Bragg grating at each connection interface member, an optical reflectometer coupled to an upstream end of the optical fiber, and an acquisition central processing unit configured to detect and locate one or more arc faults over a connection interface member by comparing the current spectral signature with the reference spectral signature of the optical fiber.
G01R 31/08 - Locating faults in cables, transmission lines, or networks
G01D 5/353 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
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 31/52 - Testing for short-circuits, leakage current or ground faults
An aircraft landing gear assembly comprising a first structural member coupled to a second structural member via a joint, the joint comprising a bearing, the bearing comprising a tubular body formed from: a metal matrix composite (MMC) comprising a metal, a carbide compound and tungsten disulphide.
F16C 17/02 - Sliding-contact bearings for exclusively rotary movement for radial load only
F16C 17/10 - Sliding-contact bearings for exclusively rotary movement for both radial and axial load
C22C 32/00 - Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
52.
METHOD FOR MANUFACTURING A PART MADE OF COMPOSITE MATERIAL
A method for manufacturing a part made of composite material includes three-dimensionally weaving a structure having a longitudinal axis (A). The method further includes the step of braiding of at least one layer of braiding threads at at least one predetermined angle relative to the longitudinal axis around the woven structure.
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 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
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]
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
An electrically interconnecting member configured to electrically join a printed circuit board belonging to a mechanical part to a piece of electrical equipment. The printed circuit board comprising output tracks. The electrically interconnecting member comprising: a contact surface configured to be fastened to the mechanical part, a free surface opposite the contact surface, input terminals placed on the contact surface and configured to be superposed on the output tracks of the printed circuit board, and output interfaces placed on the free surface at distance from the input terminals and configured to be connected to the piece of electrical equipment, at least one input terminal comprising a cavity configured to receive a conductive adhesive so as to connect together the input terminal and the output terminal when they are superposed.
The invention relates to a nickel-based alloy powder, that comprises in weight percentages, 14.00 to 15.25% of chromium, 14.25 to 15.75% of cobalt, 4.00 to 4.60% of aluminium, 0 to 0.50% of iron, 0 to 0.15% of manganese, 3.00 to 3.70% of titanium, 3.90 to 4.50% of molybdenum, 0 to 0.015% of sulphur, 0 to 0.06% of zirconium, 0.012 to 0.020% of boron, 0 to 0.20% of silicon, 0 to 0.10% of copper, 0 to 150 ppm of carbon, 0 to 0.5 ppm of bismuth, 0 to 5 ppm of lead, 0 to 1000 ppm of platinum, 0 to 1000 ppm of palladium, 0 to 50 ppm of hydrogen, 0 to 5 ppm of silver, 0 to 120 ppm of nitrogen, 0 to 1000 ppm of rhenium, 0 to 410 ppm of oxygen and 0 to 500 ppm of inevitable impurities, the rest being made up of nickel, and has a particle size D10 between 3 and 10 μm, a particle size D90 between 20 and 40 μm and a particle size D50 between 10 and 20 μm, the values of the particle sizes D10, D50 and D90 having been measured by laser diffraction according to standard ISO 13322-2. The invention also relates to a method for manufacturing a part using said powder and a resulting part.
B22F 1/10 - Metallic powder containing lubricating or binding agentsMetallic powder containing organic material
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
55.
NAVIGATION ASSISTANCE METHOD AND DEVICE BASED ON A KALMAN FILTER
Association Pour la Recherche et le Developpement des Methods et Processus Industriels-Armines (France)
Inventor
Barrau, Axel
Parellier, Colin
Bonnabel, Silvère
Abstract
Method for monitoring the navigation of a vehicle for the implementation of a navigation maneuver: the method including the steps of: estimating a magnitude by a Kalman filter from parameters, a digital model of the vehicle in its environment, and at least one measurement made by at least one sensor and associated with an uncertainty on this measurement, the magnitude serving to implement the navigation maneuver; determining at least one partial derivative value of the magnitude with respect to the at least one measurement; obtaining at least one criticality value of the at least one measurement for the estimation, from the at least one partial derivative.
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
G06F 7/544 - Methods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using non-contact-making devices, e.g. tube, solid state deviceMethods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using unspecified devices for evaluating functions by calculation
56.
METHOD FOR MONITORING THE ENGINE SPEED OF AN AIRCRAFT
INSTITUT NATIONAL DES SCIENCES APPLIQUÉES LYON : (France)
SAFRAN (France)
Inventor
Hawwari, Yasmine
Abboud, Dany
Marnissi, Yosra
El Badaoui, Mohammed
Antoni, Jérôme
Andre, Hugo
Abstract
A method for monitoring the engine speed of a rotating machine, includes constructing a raw spectrogram from a vibratory signal; denoising the spectrogram to obtain an equalised spectrogram, the denoising including a first sub-procedure of determining a foot of the spectrogram, the foot of the spectrum being a set of random harmonic components contained in the raw spectrogram, the first sub-procedure including a first sub-sub-procedure of constructing a regression function robust to the peaks of the spectrogram, the regression function being applied to a logarithm of the spectrogram or to the spectrogram; a second sub-sub-procedure of determining the foot of the spectrum from the regression function; a second sub-procedure of determining the equalised spectrogram from the foot of the spectrogram; separating sources in the equalised spectrogram by determining an estimator of the frequencies of interest; determining an instantaneous speed of rotation of the engine speed from the estimator.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Appareils, équipements et instruments électriques, électroniques et numériques pour la navigation, le guidage, le pilotage, la stabilisation, la localisation de véhicules aériens, terrestres, maritimes et spatiaux; gyromètres; équipements et appareils gyroscopiques et accélérométriques; systèmes de navigation inertielle et hybride; casques de pilotage et équipements de visualisation pour applications civiles et militaires; équipements et bases de données pour la préparation, le suivi et la restitution des missions de véhicules terrestres, aériens et maritimes; appareils de cartographie numérique; calculateurs de mission; appareils, instruments et dispositifs électriques et électroniques pour l'aéronautique; systèmes d'aide à la maintenance (ACMS); systèmes de commandes du cockpit; actionneurs de commandes de frein et d'inverseur de poussée; systèmes de contrôle de vol automatique d'aéronefs; calculateurs de commandes de vol; centrales inertielles d'attitude et de cap; appareils, instruments et équipements d'analyse de données techniques et scientifiques (station d'analyses au sol); appareils, équipements et instruments optiques pour applications scientifiques, la navigation, le guidage, le pilotage, la stabilisation de véhicules aériens, terrestres, maritimes et spatiaux; caméras infrarouges; caméras vidéo; équipements et appareils de détection optique ou infrarouge; équipements et appareils de conduite de tir; imageurs thermiques; systèmes d'observation; systèmes de veille et de poursuite infrarouge; lunettes de visées, télescope, longue vues; viseurs optiques; appareils, équipements et instruments de navigation, d'observation et de contrôle pour véhicules sans pilote à usage civil et militaire; systèmes d'observation et de reconnaissance; systèmes de transmissions et de communication sécurisées; terminaux de télécommunication et de chiffrement; réseaux sécurisés; appareils, équipements et instruments électroniques pour fantassins et personnels de sécurité; systèmes de surveillance jour/nuit; jumelles pour vision jour/nuit; batteries, accumulateurs électriques; systèmes de surveillance aéroporté; plateforme optronique gyrostabilisée et orientable; appareils et équipements pour l'acquisition, la compression, la transmission, l'analyse et la restitution d'images satellites et de photographies aériennes; systèmes de transmission d'images par liaison radio numérique; optique spatiale; optique de reconnaissance aérienne; métrologie optique; parachutes et systèmes de parachutes.
(2) Avions sans pilote, drones, véhicules aériens; planches de bord; manches de pilotage avec manette intégrée. (1) Services d'installation, de réparation et de maintenance d'équipements électroniques de véhicules terrestres, maritimes et aériens; maintenance et réparation d'équipements aéronautiques; installation, entretien et réparation d'appareils et instruments d'astronomie terrestre, d'appareils et instruments optoélectroniques pour l'industrie des lasers, des semi-conducteurs et de la défense et notamment de télescopes, miroirs, objectifs.
(2) Conception (élaboration) de logiciels et de matériel informatique; développement et conception (élaboration) de logiciels pour systèmes de navigation (GPS et ou par satellite); développement et conception de logiciels pour systèmes d'information en matière de défense; conversion de données et de programmes informatiques; conception, organisation, mise à disposition, maintenance de logiciels et de composants logiciels et fourniture en ligne de logiciels; recherche technique, scientifique et industrielle; ingénierie; recherche et développement (travaux d'ingénieurs) dans le domaine aéronautique, nautique et de la défense; analyse de données techniques; conseils techniques dans le domaine aéronautique et de la défense (travaux d'ingénieurs); service d'ingénierie opérationnelle pour compagnies aériennes; rassemblement, systématisation et stockage de données.
58.
Heating turbomachine for a fuel-conditioning system configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank
A heating turbomachine for a fuel-conditioning system, which is configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank. The heating turbomachine comprising: compressor; a turbine; a combustion chamber which is configured to discharge a flow of exhaust air loaded with heat energy and to rotate the turbine; at least one fluid circuit in which a heat-transfer fluid circulates in the downstream direction; and at least one post-combustion heat exchanger which is mounted in the fluid circuit and is configured to extract heat energy from the exhaust air chamber flow between the combustion and the turbine.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
59.
Method for attaching a part to a carrier by transfer of an adhesive film
A method for transferring an adhesive onto a part intended to be glued on a carrier, the adhesive being in the form of a double-sided film including a separator on each face, the part including an internal concave portion that does not enable uniform application of the adhesive film once the separators have been removed. The method includes attaching the adhesive film to a punch that matches the shape of the part within a range that approximately corresponds to the thickness of the adhesive film; removing the separator from the side of the adhesive film that is to be attached to the part; setting the part on the punch covered with the adhesive film that has had its separator removed; and transferring the adhesive film onto the part by creating a vacuum between the part and the punch by means of a vacuum device.
B29C 63/16 - Lining or sheathing, i.e. applying preformed layers or sheathings of plasticsApparatus therefor using sheet or web-like material applied by "rubber" bag or diaphragm
B29C 65/00 - Joining of preformed partsApparatus therefor
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
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
60.
Method for three-dimensional weaving of a fibrous structure with orientation of weft columns in a deployment portion and resulting fibrous structure
In a method for three-dimensional weaving of a fibrous structure between layers of warp yarns and layers of weft yarns, the weft yarns are woven in a plurality of columns spaced apart from one another in a longitudinal direction. The method includes weaving deployment portions in the fibrous structure that is interwoven with an adjacent portion, the weft yarns of the weft yarn columns of the adjacent portion being juxtaposed in a first stacking direction perpendicular to the longitudinal direction. During the process of weaving the deployment portions, the weft yarns of each weft yarn column are positioned against the fell of the fibrous structure in stacking directions that are different from the first stacking direction.
D03D 25/00 - Woven fabrics not otherwise provided for
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
D03D 1/00 - Woven fabrics designed to make specified articles
D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE LORRAINE (France)
OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventor
Menou, Edern
Delfosse, Jérome
Millet, Yvon
Abstract
A titanium alloy includes, in content by weight 4.0% to 5.0% aluminium; 3.50% to 4.50% tin; 1.0% to 4.0% zirconium; 2.0% to 5.25% molybdenum; 1.0% to 2.50% niobium; 0.10% to 0.25% silicon; 0.10% to 0.18% oxygen; the remainder being titanium and unavoidable impurities, the alloy further being such that the Aleq criterion, referred to as equivalent aluminium content by weight, is less than or equal to 8.5%, the Aleq criterion being defined as Aleq=[Al]+[Sn]/3+[Zr]/6+10*[O] where, [Sn], [Zr] and [O] are the contents by weight of aluminium, tin, zirconium and oxygen respectively.
A gantry crane and associated method of erection, the gantry including a frame having at least three first members; a longitudinal rail supported by the frame; and at least three second members extending between a first end portion and an opposite second end portion. Each second member can be connected to the frame by means for rigid connection and continuous rotational movement of the second member relative to the frame between a first position in which the second member forms an angle of less than 90° with the first plane and a second position in which the second member is substantially perpendicular to the first plane.
B66C 17/00 - Overhead travelling cranes comprising one or more substantially-horizontal girders the ends of which are directly supported by wheels or rollers running on tracks carried by spaced supports
B66C 23/78 - Supports, e.g. outriggers, for mobile cranes
63.
ALLOY POWDER, METHOD FOR MANUFACTURING A PART BASED ON THIS ALLOY, AND PART THUS OBTAINED
The invention relates to a titanium-based alloy powder which comprises, in percentages by weight, 32.0 to 33.5% aluminium, 4.50 to 5.10% niobium, 2.40 to 2.70% chromium, 0 to 0.1% iron, 0 to 0.025% silicon, 0 to 100 ppm carbon, 0 to 100 ppm nitrogen, 0 to 1000 ppm dioxygen, 0 to 50 ppm dihydrogen and 0 to 500 ppm unavoidable impurities, the balance being titanium, and which has a D10 particle size of between 3 and 10 μm, a D90 particle size of between 20 and 40 μm and a D50 particle size of between 10 and 25 μm, the D10, D50 and D90 particle size values having been measured by laser diffraction in accordance with standard ISO 13322-2. The invention also relates to a method for manufacturing a part using this powder and to a part thus obtained.
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 1/107 - Metallic powder containing lubricating or binding agentsMetallic powder containing organic material containing organic material comprising solvents, e.g. for slip casting
The invention relates to a system for measuring the fatigue of a mechanical structure, comprising:
a first force sensor capable of generating a first signal representative of a force applied to a first mechanical part of the mechanical structure;
a second force sensor capable of generating a second signal representative of a force applied to a second mechanical part of the mechanical structure; and
an electronic processing module configured to calculate a correlation coefficient between the first signal and the second signal, and to indicate a state of fatigue of the mechanical structure as a function of a temporal change in the previously calculated correlation coefficient.
A method for producing a magnet for a rotor of an electric machine has a first phase of producing a magnet blank which includes a step of pressing powders into a magnet mold in the presence of a magnetic field while subjecting the powders to a magnetic field generated by a first magnetization tool. The method further includes a step of densifying the obtained magnet blank and a second phase. The second phase includes finishing the magnet blank by at least one final magnetization step in order to obtain a magnet. The mold is arranged in a densifying chamber, and the densifying step is carried out by flash SPS sintering in the densifying chamber.
A method for detecting defects for an aeronautical part, includes training, during a plurality of epochs, an artificial neural network to supply a defect probability for each pixel of an image, for each epoch and for each image of a validation set, creating a defect probability matrix based on defect probabilities for each pixel of the image, for each epoch, determining, for each image of the validation set, based on the defect probability matrices, a curve of defect detection as a function of false alarms, determining a set of the N best epochs on the basis of the defect detection curves and of a business criterion, for each epoch of the N best epochs, inspecting the image to be inspected by applying the artificial neural network with parameters associated with the epoch, so as to obtain an inspected sub-image associated with the training epoch.
G06V 10/75 - Organisation of the matching processes, e.g. simultaneous or sequential comparisons of image or video featuresCoarse-fine approaches, e.g. multi-scale approachesImage or video pattern matchingProximity measures in feature spaces using context analysisSelection of dictionaries
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
67.
METHOD FOR MAKING A THIN-WALLED ACOUSTIC COMPONENT
A method for making an acoustic component includes a plurality of hollow complex acoustic elements, the method including heating a film of thermoplastic material to a first temperature above the glass transition temperature of the film; shaping the heated film of thermoplastic material in a tool including a mould which has a plurality of mould cavities having a shape corresponding to the shape of the complex acoustic elements of the acoustic component to be made, the heated film of thermoplastic material being shaped locally in each of the mould cavities, at least the mould being kept at a second temperature above the glass transition temperature of the thermoplastic material; cooling the mould; and removing a complex acoustic multi-element panel including a plurality of hollow complex acoustic elements from the mould.
An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.
A propeller blade or airfoil of a turboprop of composite material includes a fibrous reinforcement densified by a matrix, the propeller blade or airfoil including, in a span direction, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic preform portion present in the aerodynamic profile, the root and aerodynamic preform portions being linked to one another by the three-dimensional weave. The root preform portion of the fibrous preform includes an unlinked area delimiting an internal root recess forming a cavity opening at a free end of the root.
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
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
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]
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
70.
Propeller blade or airfoil with wound composite root
A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including along a longitudinal direction a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile parts being connected to one another by three-dimensional weaving. The root preform part includes two woven skins wound around an insertion element.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventor
Cavarroc, Marjorie Christine
Poulon, Angéline Nadine Jeanne
Mauvy, Fabrice Claude Michel
Achille, Aurélie Corinne
Michau, Dominique Paul Abel
Fourcade, Sébastien
Abstract
A component for a solid-oxide electrolyte fuel cell or electrolyser provided with an anticorrosion coating, as well as such a solid-oxide electrolyte fuel cell or electrolyser, the component including an electrically conductive substrate, and an anticorrosion coating deposited on at least one surface of the substrate, the anticorrosion coating including at least one main tantalum-nitride-based layer doped with one or more dopant elements chosen from the family of the transition metals or lanthanides.
H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
H01M 8/1246 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides
An aircraft landing gear shock absorber strut (50) comprising: an outer cylinder (26) having an inner surface defining a cylinder bore extending into the outer cylinder from a first axial face of the outer cylinder, the cylinder bore defining an oleo-pneumatic chamber containing a damping liquid and a gas which can mix within the cylinder bore; a sliding tube (28) including a first end portion movably mounted within the cylinder bore so as to be movable along the cylinder bore between a compressed position, in which a second end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder, and an extended position, in which the second end portion of the sliding tube is relatively far from the first axial face of the outer cylinder, the sliding tube including a tube bore extending into the sliding tube from the first end portion, the tube bore being arranged in fluid communication with the cylinder bore to exchange the damping liquid with the cylinder bore; an elongate metering pin (34) having a longitudinal axis and including an axial channel for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position; and a flow restricting plate (52) including: a first portion (52a) provided with a first damping orifice (DO) in which the metering pin is located and through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions to vary the free space cross sectional area of the first damping orifice to control an axial flow of the damping liquid (J) moving from the tube bore to the cylinder bore as the sliding tube moves from the extended position towards the compressed position; and a second portion (52b) provided with a second damping orifice (DO2) for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position to define a second flow of the damping liquid (J2), wherein the second damping orifice is orientated to direct the second flow of damping liquid towards the axial channel of the metering pin to disrupt the axial flow of damping liquid.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/342 - Throttling passages operating with metering pins
F16F 9/48 - Arrangements for providing different damping effects at different parts of the stroke
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventor
Cavarroc, Marjorie Christine
Mauvy, Fabrice Claude Michel
Poulon, Angéline Nadine Jeanne
Achille, Aurélie Corinne
Michau, Dominique Paul Abel
Fourcade, Sébastien
Abstract
A component for an acid electrolyte fuel cell or electrolyser provided with an anticorrosion coating, as well as such an acid electrolyte fuel cell or electrolyser, the component including an electrically conductive substrate, and an anticorrosion coating deposited on at least one surface of the substrate, the anticorrosion coating including at least one main tantalum-nitride-based layer doped with one or more dopant elements chosen from the family of the transition metals or lanthanides.
An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.
A drive circuit for a plurality of piezo-actuated hydraulic pumps for an aircraft, and a hydraulic pump system implementing the same. The drive circuit includes a voltage boost stage that receives a DC input supply voltage and delivers an increased DC output voltage to a high voltage, HV, link point; a plurality of inverter stages coupled in parallel at the HV link point that receive DC voltage from the HV link point and generate an oscillating output voltage for driving a respective piezo-actuated pump; and a control system that controls the output voltage and phase of the inverter stages to drive the plurality of piezo-actuated pumps out of phase. The control system measures the power consumption of each piezo-actuated pump and regulates the output voltage of at least one of the inverter stages to balance the power consumption of each piezo-actuated pump.
A method for manufacturing a panel including a plurality of partitions defining cells covered by at least one skin, the skin being formed by draping fibrous structures impregnated with a thermoplastic material on the upper edges of the partitions by automatic placement of fibers, the upper edges of the partitions and the fibrous structures being joined together with the aid of a localized heating device at the moment they are placed in contact, the method wherein the fibrous structures are draped with a draping tension on the interface between each edge of a partition and the deposited fibrous structure applying a shear stress of between 50% and 80% of the maximum shear stress before rupture of the interface.
B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 41/00 - Arrangements for controlling or monitoring lamination processesSafety arrangements
77.
Device for assisting with regulation of propellers of aeronautical turbomachinery
This control device for a propulsion system, comprising means for calculating a blade-pitch setpoint of at least one propeller of the propulsion system, the calculation means using a performance predictive model of the propeller taking account of at least one flight speed for adapting a blade-pitch angle setpoint, is characterised in that the performance predictive model of the propeller is configured to use polar charts implemented in the form of a mathematical law.
A nickel-based superalloy including in weight percentages: 5.0 to 6.5% aluminium, 0.50 to 2.5% tantalum, 1.50 to 4.0% titanium, 0 to 7.0% cobalt, 12.0 to 16.0% chromium, 0.50 to 2.5% molybdenum, 0 to 2.0% tungsten, 0.05 to 0.15% hafnium, 0 to 0.15% silicon, the remainder consisting of nickel and unavoidable impurities. A single-crystal blade including such an alloy and to a turbomachine including such a blade.
An assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction.
Retaining members hold the cores in position in the injection mold.
B22D 17/24 - Accessories for locating and holding cores or inserts
B22D 25/02 - Special casting characterised by the nature of the product by its peculiarity of shapeSpecial casting characterised by the nature of the product of works of art
80.
SYSTEM AND METHOD FOR CONDITIONING FUEL FOR AN AIR-BREATHING HYDROGEN ENGINE
A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.
An aircraft landing gear assembly (36) comprising a wheel and brake assembly and a shock absorbing strut (37), the strut including a mounting bearing for movably coupling the aircraft landing gear assembly to an aircraft for movement between a stowed condition for flight and a deployed condition for take-off and landing, the aircraft landing gear assembly further comprising: a noise-inducing region (37); a first perforated sheet fairing (1n); and a second perforated sheet fairing (3n) arranged downstream of the first perforated sheet fairing when the landing gear is in the deployed condition.
A method for producing a part, in particular a part made of composite material, in particular for a turbomachine, including at least: a step of producing a preform, during which a fibrous preform intended to form an outer skin of the part is produced; a step of producing a core, during which a rigid core, in particular a hollow rigid core, intended to form a framework of the part is produced; an insertion step, during which the rigid core is inserted into the fibrous preform, an injection step, during which a matrix is injected into the fibrous preform; and a heat-treatment step, during which polymerisation of the matrix is carried out.
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]
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29K 71/00 - Use of polyethers as moulding material
B29K 77/00 - Use of polyamides, e.g. polyesteramides, as moulding material
B29K 79/00 - Use of other polymers having nitrogen, with or without oxygen or carbon only, in the main chain, as moulding material
83.
SYSTEM FOR COOLING A LIQUID FOR LUBRICATING AN AIRCRAFT TURBOMACHINE
A system for cooling a liquid for lubricating an aircraft turbomachine, includes an exchanger including a cooling volume and a circuit for cooling a heat-transfer fluid by a loop for circulating the two-phase fluid, with thermocapillary pumping. The cooling circuit includes a condenser including channels connected in parallel to one another in order to make it possible to cool the fluid circulating in the condenser from a vapour state to a liquid state, a first capillary evaporator of the exchanger in order to absorb the heat of the lubricating liquid in the first volume, the first evaporator including a capillary porous wick for separating the heat-transfer fluid in the two-phase state between a liquid state and a gaseous state by a capillary pressure jump.
A method includes receiving an operating setpoint for an electrical power source, receiving a measurement of a voltage of an electrical bus connecting the electrical power source to an electrical receiver, comparing the measurement of the voltage with a template having limits of change over time for the voltage, and controlling the electrical power source such that if the measurement of the voltage lies within the limits of the template, the electrical power source applies the operating setpoint, and if the measurement of the voltage lies outside the limits of the template, the electrical power source regulates the voltage so as to restore the voltage to within the limits of the template. The method is implemented by a controller of the electrical power source.
H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
H02P 101/25 - Special adaptation of control arrangements for generators for combustion engines
H02P 101/30 - Special adaptation of control arrangements for generators for aircraft
85.
Method for producing a bladed component for an aircraft turbine engine
A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising including a blade which has a stacking axis and at least one longitudinal end of which is connected to a transverse platform, the method including the steps of: a) producing a fibrous preform, this preform including a first part that is intended to form a blade and at least one second part that is intended to form a platform, this second part of the preform including a disconnect that defines two stacked portions that are separated by a disconnect surface that is substantially parallel to the axis, b) folding the portions, respectively, on two opposing sides of the first part, and c) stiffening the preform.
09 - Scientific and electric apparatus and instruments
35 - Advertising and business services
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Appareils pour l'enregistrement, la transmission, la reproduction ou le traitement de sons, images ou données; équipement pour le traitement de l'information et les ordinateurs; logiciels, périphériques d'ordinateurs; appareils et instruments scientifiques et de recherche basés sur l'analyse automatique d'informations géospatiales; équipements de traitement de données; équipements de traitement de données basés sur l'analyse automatique d'informations géospatiales; logiciels d'intelligence artificielle; logiciels d'intelligence artificielle pour le traitement automatique d'images satellites; dispositifs et supports de stockage des données et images; bases de données; logiciels de gestion de bases de données. (1) Services annexes liés à la gestion ou au traitement des données, y compris la gestion de bases de données et plus spécifiquement services d'analyse de données pour assister les clients dans leurs processus de prise de décision; fourniture d'informations d'affaires dans le domaine stratégique et militaire; analyses commerciales stratégiques dans les domaines de la défense et de la sécurité.
(2) Fourniture d'accès à des bases de données, transmission de données, distribution électronique d'images satellite via un réseau informatique.
(3) Recherche et développement de nouveaux produits (pour des tiers); étude de projets techniques; élaboration (conception), installation, maintenance, mise à jour ou location de logiciels; programmation pour ordinateurs; consultation en matière de logiciels informatiques; conversion de données ou de programmes informatiques (autres conversions physiques); conseil technologique dans le domaine de l'intelligence artificielle; plates-formes pour intelligence artificielle en tant que logiciel-service [SaaS]; recherche dans le domaine de la technologie de l'intelligence artificielle; fourniture de programmes informatiques d'intelligence artificielle; développement et test de méthodes, d'algorithmes et de logiciels informatiques.
09 - Scientific and electric apparatus and instruments
35 - Advertising and business services
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus for sound, image or data recording, transmission, reproduction or processing; equipment for data processing and computers; downloadable software for monitoring and tracking the location of goods and people, mapping geographic areas, operating system, communication, electronic position, location, and computer peripheral devices; scientific and research apparatus and instruments based on automatic analysis of geospatial information, namely, downloadable software and algorithms; data processing equipment; data processing equipment based on the automatic analysis of geospatial information; downloadable artificial intelligence software for analyzing high-resolution imagery, full motion video and acoustic signals; downloadable artificial intelligence software for automatic processing of satellite images; data and image storage media in the nature of downloadable database management software and devices in the nature of data processing equipment ; downloadable databases in the field of artificial intelligence, defense, security, space and aerospace; downloadable database management software; All of the foregoing goods are exclusively used in the fields of artificial intelligence, defense, security, space and aerospace. Services related to data management or processing, including database management and more specifically data analysis services to assist customers in their decision-making processes; providing business information in the strategic and military field; strategic business analysis in the fields of defense and security. Providing access to databases, data transmission, electronic distribution of satellite images via a computer network. Research and development of new products for others; technical project study, namely, conducting scientific feasibility studies, engineers' services; development, installation, maintenance, updating or rental of software for use in database management, mapping, location, change detection and monitoring, tracking, site surveillance, digital database analysis, and the automatic analysis of geospatial information; programming for computers; consultancy relating to computer software; conversion of computer programs and data, other than physical conversion; technological advice in the field of artificial intelligence technology; platforms for artificial intelligence, namely Software as a service (SAAS) services featuring software for the automatic analysis and compilation of geospatial information in the field of artificial intelligence, defense, security, space and aerospace ; research in the field of artificial intelligence technology; providing downloadable computer programs for artificial Intelligence for artificial Intelligence analytics solutions for high-resolution imagery, full motion video and acoustic signals ; development and testing of computing methods, algorithms and software; All of the foregoing services are exclusively used in the fields of artificial intelligence, defense, security, space and aerospace.
The invention relates to a nickel-based alloy comprising, in weight percent: 4.0 to 20.0% cobalt, 14.0 to 18.5% chromium, 1.8 to 2.6% aluminum, 1.3 to 1.9% titanium, 5.5 to 6.5% tantalum, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
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
A nickel-based alloy includes, in weight percent: 4.0 to 15.7% cobalt, 15.3 to 19.5% chromium, 1.6 to 5.45% molybdenum, 1.65 to 2.5% aluminum, 2.8 to 4.3% titanium, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
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
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
A process for additive manufacturing of a part by successive deposition of layers of powder layers is provided. The process steps are performed within a manufacturing machine having a preparation zone for at least one layer and a consolidation zone for the powder, offset from each other. The process includes: (a) preparing at least one layer comprising at least two zones filled with at least two different powders, e.g., of different materials and/or particle sizes, in the preparation zone; (b) moving the at least one layer into the consolidation zone; (c) placing the at least one layer on either a manufacturing support or on an already consolidated portion of the part; and (d) consolidating at least one portion of the at least one layer by sintering, by melting, or by adding a binder.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
A heat exchanger for a turbomachine, in particular an aircraft turbomachine, having a longitudinal axis, including a supporting wall extending in a first direction; a plurality of fins, each of which rises in a second direction from the supporting wall and being intended to be swept by an air stream, and a profiled panel covering the fins and extending in the first direction between a first diverging-profile wall upstream of the fins and a second converging-profile wall downstream of the fins. The heat exchanger includes an air intake device configured to slow the air stream in a third direction, the device having multiple separate air intake openings which are arranged upstream of the fins in the first direction and which are distributed in the third direction.
A vane for an aircraft turbomachine includes a blade and a cooling circuit inside the blade. The cooling circuit has at least one longitudinal flow cavity of a cooling air stream (RF). The cooling circuit further includes elements that protrude into the cavity and are configured to disrupt the air stream. Each of the protruding elements is generally arc-shaped and internally defines, with a first wall, a first cross-sectional flow area, and externally, with a second wall opposite the first wall, a second cross-sectional flow area. Each of the elements is configured such that the first or second cross-sectional flow area is reduced from upstream to downstream relative to the direction of the air stream.
An apparatus for providing energy in an aircraft, including a DC bus; at least one low-pressure electrical source and at least one high-pressure electrical source. The apparatus further includes a system for calculating a droop gain for each electrical source, based on at least one operating characteristic of the turbine engine; and for each electrical source, a model for controlling the electrical source in question, which module is designed to implement a droop setting based on the droop gain calculated for the electrical source in question.
A heat exchanger of the air/oil type, for an annular air stream of a turbomachine, comprising a heat exchange zone with oil passages and heat exchange surfaces with the air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and included in a plane perpendicular to said air flow, said profile of the exchange zone thermal being in an arc of a circle so as to be able to be arranged in the annular air stream, remarkable in that said heat exchanger comprises on a radially internal or external face of the exchange zone thermal, an oil inlet and an oil outlet, the oil passages comprising several paths between said oil inlet and said oil outlet, distributed along the profile in circular arc of the heat exchange zone.
Method for manufacturing a blade made of a composite material for a turbomachine, in particular of an aircraft, including steps of: a) arranging a preform produced by three-dimensional weaving of fibres within a mould, a polymerisable adhesive being inserted between a shield and an edge of the preform, b) closing and heating the mould, then injecting the polymerisable resin into the mould, wherein the mould is heated according to a cycle including increases in temperature from T1 to T2, then from T2 to T3, and in that the resin is injected in step b) during or just before the increase in temperature from T2 to T3, the temperature T2 being selected so that the viscosity of the adhesive is greater than the viscosity of the resin.
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29K 63/00 - Use of epoxy resins as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A process carrying out non-planar three-dimensional forming of at least one segment of a flexible printed circuit board including an electrically insulating polymer film, and, on at least one side of the polymer film, a metallization then carrying out electrodeposition in which a conductive layer is deposited on at least the metallization of at least the formed segment.
H05K 3/18 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using precipitation techniques to apply the conductive material
97.
METHOD FOR DIMENSIONING A MULTI-POLE ORIENTED-FLUX MAGNETIC RING, AND ASSOCIATED ROTOR, ROTATING ELECTRIC MACHINE AND AIRCRAFT
The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, where the magnetic ring includes a predetermined number of pairs of poles, and the magnetic ring is formed by at least one oriented-flux magnet. The method includes determining a characteristic dimension of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, determining a reference value equal to the minimum value out of a predetermined reference length and twice the value Pi, comparing the characteristic dimension of the magnet with the reference value, and if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.
An axial turbomachine includes a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called a secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the tertiary flow being in a tertiary flow vein radially external to the primary flow, delimited by an internal wall and an external wall; and an air/oil type heat exchanger, disposed in the tertiary flow vein. The heat exchanger includes several angular sectors, each angular sector including an oil inlet on the internal wall at an angular end of the sector, and an oil outlet on the internal wall at an opposite angular end of the sector.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
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 3/06 - 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
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
99.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
An axial turbomachine comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a flow of radially external air, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow flow in a tertiary flow vein radially external to said primary flow; and a heat exchanger disposed in the tertiary flow vein. The heat exchanger extends radially and axially in an upstream section section of the tertiary flow vein, having a divergent longitudinal section, said tertiary flow vein comprises a downstream section presenting a converging longitudinal section, following the tertiary flow.
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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
100.
Method for producing composite blade cleats for an aircraft turbine engine
Method for manufacturing composite blade cleats for an aircraft turbine engine, including providing a woven panel, including a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least a portion of the margin in common; injecting a matrix onto the panel; after injection, dividing the panel in order to separate the cleats from one another; machining the cleats to remove the margins.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
