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 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
17.
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 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
24.
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
25.
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
26.
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
29.
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
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
33.
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
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
36.
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
37.
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.
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
43.
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
44.
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
45.
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
48.
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
49.
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.
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
51.
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
52.
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.
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
58.
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.
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
60.
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
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.
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
64.
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.
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 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
68.
METHOD FOR PRODUCING A PART, IN PARTICULAR A PART MADE FROM A COMPOSITE MATERIAL
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
69.
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
71.
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.
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.
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
80.
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.
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
82.
System for converting and transporting electrical energy for the internal hybridisation of an aircraft turbomachine
a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
83.
Device and method for depositing thick metal nitride coatings by the supercritical fluid route
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
Inventor
Cavarroc, Marjorie Christine
Aymonier, Cyril
Giroire, Baptiste Simon
Guillaume, Bertrand
Poulon, Angélique Nadine Jeanne
Aubert, Guillaume
Abstract
A device for depositing a thick metal nitride on a sample by supercritical fluids includes a first enclosure forming a first closed volume; a second enclosure placed in the first enclosure and delimited by internal walls transparent to electromagnetic radiation forming a second closed volume intended to comprise a fluid under supercritical conditions; a heat transfer dielectric fluid circulating in the first volume around the second enclosure; a sample holder present in the second volume; an induction heating device surrounding the second enclosure; inlets for introducing a fluid and at least one precursor material into the second enclosure; and an outlet to purge the second volume.
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
84.
Fuel conditioning system for supplying an aircraft turbomachine, and method of supplying a turbomachine
A fuel conditioning system configured to supply an aircraft turbomachine with fuel from a cryogenic tank. The conditioning system comprising a primary heat exchanger designed to heat the fuel flow to at least one primary temperature, and at least one secondary heat exchanger, mounted downstream of the primary heat exchanger, designed to heat the fuel flow to at least one secondary temperature higher than the primary-temperature, the primary heat exchanger being configured to extract calories in the fuel flow that is at least at the secondary temperature.
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 7/224 - Heating fuel before feeding to the burner
85.
System for conditioning fuel for supplying an aircraft turbomachine, aircraft and method of use
A fuel conditioning system configured to supply a turbomachine with fuel from a cryogenic tank, the conditioning system comprising a fuel circuit connected at the inlet to the cryogenic tank and at the outlet to the turbomachine, a pump, a fuel cell configured to provide electricity to an electrical network of the aircraft, at least a first heat exchanger belonging to the fuel circuit and configured to transmit calories from the fuel cell to the fuel flow in order to heat it, and at least one second heat exchanger mounted downstream of the first heat exchanger in the fuel circuit and configured to transmit calories from the turbomachine to the fuel flow in order to heat it.
B64D 41/00 - Power installations for auxiliary purposes
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 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
F02C 7/224 - Heating fuel before feeding to the burner
86.
Application head for automatically applying fibres
Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
87.
FACILITY AND METHOD FOR PAIRING A SHIELD TO A PREFORM FOR THE PRODUCTION OF AN AIRCRAFT TURBINE ENGINE VANE
A facility for pairing a metal shield to a leading edge of a preform made of composite material for the production of an aircraft turbine engine blade, the facility including a support configured to receive and hold the metal shield, —a movement hexapod which carries the support and is able to move the support along and about the three axes of an XYZ coordinate system, —an automaton which includes jaws and is configured to receive and hold the preform, and—a computing unit for controlling the hexapod and the automaton with a view to producing the pairing. The invention also relates to a method for pairing the metal shield to the leading edge of the preform made of composite material for the production of the aircraft turbine engine blade.
An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.
A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
90.
Curing mold for manufacturing a turbomachine component made of composite material from a preform and method for producing a component by means of such a mold
The invention relates to a curing mold (10) for manufacturing a turbomachine component made of composite material from a preform (200), comprising: —a first and a second body (11, 12) defining an air gap receiving the preform; —at least one primary channel (21) arranged in the first and/or the second body; —an injection member (22) of a pressurized fluid in the primary channels; —at least one secondary channel (23), in which a piston (24) slides, which delimits, on the one hand, a first chamber (26) in communication with the or a primary channel and, on the other hand, a second chamber (27) in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.
B29C 43/34 - Feeding the material to the mould or the compression means
B29C 43/02 - Compression moulding, i.e. applying external pressure to flow the moulding materialApparatus therefor of articles of definite length, i.e. discrete articles
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 43/32 - Component parts, details or accessoriesAuxiliary operations
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
A method for manufacturing a shell mold intended for manufacturing at least one metal part by lost-wax casting, the shell mold including at least one molding cavity intended for molding the metal part, and at least one feed channel intended to convey a liquid metal to the molding cavity, the method including manufacturing a wax pattern including a part pattern intended to form the molding cavity and a feed channel pattern intended to form the feed channel, arranging at least one ceramic insert around at least a portion of the feed channel pattern, and manufacturing the shell mold around the wax pattern.
The invention relates to a thermocouple comprising: —a substrate comprising an upper surface; —a first arm comprising a first horizontal part and a first connection terminal; —a second arm comprising a second horizontal part and a second connection terminal; the first arm being arranged on the upper surface of the substrate, the second arm being arranged on the first arm such that the second horizontal part at least partially covers the first horizontal part and such that the second connection terminal is in contact with the upper part of the substrate, a hot junction of the thermocouple being defined by the zone of contact between the first arm and the second arm.
G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
G01K 1/14 - SupportsFastening devicesArrangements for mounting thermometers in particular locations
H10N 10/13 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the heat-exchanging means at the junction
H10N 10/17 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the structure or configuration of the cell or thermocouple forming the device
93.
POWER MODULE HAVING SEMICONDUCTOR COMPONENTS AND INCORPORATING A TEMPERATURE SENSOR, AND ASSOCIATED MANUFACTURING METHOD
A power module includes a plurality of semiconductor-based power components and a substrate having an upper metallization receiving the components and a lower metallization opposite to the upper metallization. Optionally, a baseplate may be fixed to the lower metallization of the substrate. A metal structure is in direct contact with a lower surface defined by the either optional baseplate or the substrate, on the side opposite the components. The power module includes at least one elongated temperature sensor, at least partially immersed in the metal structure and spreading parallel to the lower surface.
H01L 23/36 - Selection of materials, or shaping, to facilitate cooling or heating, e.g. heat sinks
G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
H01L 21/48 - Manufacture or treatment of parts, e.g. containers, prior to assembly of the devices, using processes not provided for in a single one of the groups or
H01L 23/00 - Details of semiconductor or other solid state devices
H01L 23/057 - ContainersSeals characterised by the shape the container being a hollow construction and having an insulating base as a mounting for the semiconductor body the leads being parallel to the base
H01L 23/538 - Arrangements for conducting electric current within the device in operation from one component to another the interconnection structure between a plurality of semiconductor chips being formed on, or in, insulating substrates
H01L 25/00 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices
H01L 25/065 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices all the devices being of a type provided for in a single subclass of subclasses , , , , or , e.g. assemblies of rectifier diodes the devices not having separate containers the devices being of a type provided for in group
94.
Method for controlling the energy set-up of a hybrid propulsion system
A method of control of a power generation and control system of an aircraft including: a hybrid propulsion system including an electrical network and a propulsive energy source, at least one non-propulsive energy source, a control unit of the hybrid propulsion system, and an overall aircraft power control unit, characterized in that the method includes: the determination of an operability limit of the propulsive energy source, the monitoring of the operability of the propulsive energy source by the control unit of the hybrid propulsion system, and the control of a power generated by the propulsive energy source by the overall aircraft power control unit when the operability of the propulsive energy source is less than said determined operability limit or the control of a power generated by the propulsive energy source by the control unit of the hybrid propulsion system.
The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current.
The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current.
The invention also relates to an aircraft provided with such a propulsion system.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
ECOLE NORMALE SUPERIEURE PARIS-SACLAY (France)
Inventor
Fragnaud, Cédric
Roux, Stéphane
Betancur, Julian
Abstract
The invention relates to a method for non-destructively testing a part by means of transmission radiography, which method comprises the following steps of acquiring N projections (P(n)) of the part, generating calculated N images (P(n)) of the part, estimating, by successive iterations, the vector p from an initial vector p=pini and the vector c from an initial vector c=cini and/or the parameter vector a from an initial vector α=αini, by minimising the sum of the squared differences between the projections (P(n)) and the images (P(n)), processing the projections (P(n)) and/or the images (P(n)), identifying defects in the part by comparing the processed projections (P(n)) and the processed images (P(n)).
An extrusion head for additive manufacturing includes an enclosure defining a supply chamber. The enclosure includes at least one inlet port opening into the supply chamber and configured to receive a material to be extruded under pressure and a plurality of extrusion nozzles. Each nozzle is in communication with the supply chamber and opens onto the exterior of the enclosure via an outlet orifice. The nozzles of the plurality of nozzles are arranged adjacent to one another with a determined spacing between each nozzle outlet orifice.
B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
A system for conditioning fuel configured to supply a main turbomachine, based on fuel from a cryogenic tank, comprising a pump configured to operate at a predetermined constant speed, at least one heat exchanger, a supply member for supplying the main turbomachine with a fuel flow, the supply member being configured to deliver a nominal flow rate when the pump is operating at a predetermined constant speed, at least one buffer tank, a first valve for controlling the supply of fuel to the buffer tank, a second valve for controlling the distribution of the fuel flew flow and a regulating device that is configured to open the second valve when the setpoint flow rate is higher than the nominal flow rate.
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 9/32 - Control of fuel supply characterised by throttling of fuel
99.
METHOD FOR DETECTING A BEARING DEFECT IN A ROTATING SYSTEM AND MONITORING SYSTEM IMPLEMENTING THIS METHOD
A method for detecting a defect in a bearing of a rotating system, includes acquiring a bearing position signal, a vibratory signal from the bearing and a theoretical characteristic vector of the bearing; determining a deterministic part of the vibratory signal and removing the deterministic part to obtain a residual signal function of the position signal; calculating, from the theoretical characteristic vector, lower and upper bounds of defect frequencies; calculating, from the vibratory signal, a spectral coherence and the square of the amplitude of the spectral coherence; calculating, from the square of the amplitude of the spectral coherence and the lower and upper bounds of the defect frequencies, a current characteristic vector of the bearing; determining a spectral cyclic contrast of the defect; finely identifying signatures of interest by calculating a weighted integrated cyclic coherence associated with the defect, and determining diagnostic indicators easily interpretable by an operator.
This method for determining a frictional coefficient of an aircraft on a runway includes the steps of:
producing a database of frictional coefficients simulated for various types of aircraft and various runway conditions by applying simulation data to models representing the braking of aircraft when landing, for various braking scenarios; and
predicting a frictional coefficient from real data of the aircraft for which the frictional coefficient is determined from data stored in the database.
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
patents
