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 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
The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to provide a separation; c) the cut preform is deformed so as to provide an orifice then comprising a first and a second open end (27a, 27b); d) the deformed preform is placed into an injection mould; e) a resin is injected in order to impregnate the whole of the deformed preform; f) the resin is polymerised; and g) a composite part is extracted from the mould; characterised in that: h) a flexible mandrel (31) with a predetermined shape is positioned in the orifice before the injection step e); i) the flexible mandrel (31) is removed after step f) or the demoulding step g), the composite part then having a hollow core (25).
F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
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]
3.
STEEL PART FOR AN AIRCRAFT AND METHOD FOR MANUFACTURING SAME
The invention relates to a method for manufacturing a steel part (10) for an aircraft, the method comprising the welding of at least two steel elements (12, 14) to one another so as to form this part (10), the application of a resistance treatment to the part (10) which comprises austenitization (30) followed by quenching (32) and at least one step of tempering (34), and the local application, to a weld bead (16) between the at least two elements (12, 14), of a softening treatment comprising heating the weld bead (16) to a softening temperature lower than the temperature Ac1 at which the steel starts to transform from ferrite into austenite.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
This invention relates to a superconducting electric machine (1), for example with axial flux or with radial flux, comprising an inductor (3) comprising superconducting pellets (7) circumferentially distributed around an axis (X) of the electric machine (1) and a flux barrier (12) comprising a superconducting material, said flux barrier (12) being centered on the axis (X) of rotation and extending radially inward of the superconducting pellets (7).
The present invention relates to a superconducting electric machine (1) comprising an inductor (3) having: —superconducting pellets (7) circumferentially distributed about an axis (X) of the electric machine (1), —an armature (2) comprising coils (5), each coil (5) having a circumferential radially inner edge (10) and a circumferential radially outer edge (9), and—at least one flow barrier (12, 12′) extending circumferentially with respect to the axis (X), each flow barrier (12) extending between the superconducting pellets (7) and the armature (2) so as to at least partially cover at least one of the radially outer edge (9) and the radially inner edge (10) of all or part of the coils (5) of the armature (2).
A method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in a casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L1, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L2, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10−4 m/s in the drawing direction. The present disclosure also relates to a plant having one or more devices for implementing the method.
B22D 41/015 - Heating means with external heating, i.e. the heat source not being a part of the ladle
B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
B22D 11/112 - Treating the molten metal by accelerated cooling
B22D 11/14 - Plants for continuous casting, e.g. for upwardly drawing the strand
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould
The invention relates to a method for monitoring the state of mechanical components such as bearings and gears on a shaft line equipping a rotating machine. Said method includes a step of obtaining at least one measurement yc[k] of the absolute acceleration of the shaft, as well as a set of steps of: obtaining a value fr[k] of the rotational frequency of the shaft, determining a matrix H[k] making it possible to define a state model described by: [k+1]=x[k]+w[k]etY[k]=[(y_c [k])¦SE[k]]=H[k]×x[k]+v[k], determining an estimator of the vector x[k] based on data from the state model, said set of steps further including, for at least one mechanical component, steps of: determining, from said estimator, a quantity characteristic of a contribution of said component to the vector Y[k], comparing said quantity with a threshold, detecting a possible defect of said at least one mechanical component.
The present invention relates to a method for manufacturing a part, comprising the steps of chemically etching, in a wet acid medium, at least a portion of a surface of a substrate made of a monocrystalline superalloy, comprising at least one element chosen from rhenium and ruthenium, the substrate having a γ-γ′ phase, the substrate having an average mass fraction of rhenium and/or ruthenium greater than or equal to 3%, the chemical etching being done in such a way that the average mass fraction of rhenium and/or ruthenium over the portion of the surface of the substance is less than 2%, and a step of depositing on the portion of the substrate a protective coating having a γ-γ′ phase and an average mass fraction of rhenium and/or ruthenium of less than 1%.
The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.
A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots
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
11.
METHOD AND DEVICE FOR CHECKING THE COMPLIANCE OF A WORKPIECE
Method for checking the compliance of a workpiece, comprising the following steps: estimating a risk of non-compliance of characteristic on the basis of a law of probability associated with the characteristic; and verifying whether the estimated risk of non-compliance satisfies a decision criterion and, if so, declaring that the workpiece is compliant for characteristic; if not, measuring a value of the characteristic, determining whether or not the workpiece is compliant based on the measured value, and updating the law of probability associated with characteristic based on the measured value.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)
12.
CIRCUIT FOR CONTROLLING POWER TRANSISTORS OF AN INVERTER ARM
A control circuit for a first switch includes at least one transistor, the first switch being arranged in series with a second switch in an inverter arm of an electrical power supply device supplying a load connected to the mid-point of the series arrangement of the first and second switch. The control circuit is configured to adjust the gate-source voltage of the at least one transistor of the first switch according to a control scheme including, during a deactivation period of the first switch, the increase of the gate-source voltage in a time window including the deactivation of the second switch and the reduction of the gate-source voltage in a time window including the activation of the second switch.
H02M 7/539 - Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters with automatic control of output wave form or frequency
B64D 41/00 - Power installations for auxiliary purposes
H02M 1/088 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters for the simultaneous control of series or parallel connected semiconductor devices
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
13.
HYBRID TURBOFAN ENGINE FOR AN AIRCRAFT, COMPRISING A MOTOR/GENERATOR COOLED BY HEAT PIPES
A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.
There is described an aircraft landing gear including an impact shield for protecting a first element of the landing gear from debris impact, the shield being pivotably connected to a second element of the landing gear different from the first element and configured to be moveable between first and second positions, wherein in the first position the impact shield is configured to deflect incident debris away from the second element of the landing gear, the impact shield being arranged to be in the first position when the landing gear is deployed/extended, and wherein the impact shield is arranged to be in the second position when the landing gear is stowed/retracted. By providing a moveable impact shield the shield can be configured to provide the desired impact protection when the landing gear is deployed, yet also minimise the space required in the landing gear bay when the landing gear is stowed. 20
Method for manufacturing an aeronautical part by additive manufacturing, the part to be manufactured extending around a central axis and comprising at least two walls angled with respect to one another and connected to one another by means of at least one connection section comprised in a connection plane perpendicular to the central axis, the method comprising: providing a digital model of the part to be manufactured, orienting the digital model with respect to a vertical construction direction of the part so that the central axis of the part has an angle β of between 0.1° and 1°; and manufacturing the part by additive manufacturing from the digital model obtained in the orientation step.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Schneider-Die-Gross, Julien Paul
Jailin, Clément
Mendoza Quispe, Arturo
Roux, Stéphane
Abstract
Method for processing a plurality of X-ray tomography volume images each associated with a part, the plurality of volume images comprising a reference volume image, including:
a step of correlating volume images to obtain a displacement field between each image and the reference image, to obtain a plurality of displacement fields minimizing the difference between the volume images,
a processing by a dimensionality reduction method of the plurality of the image displacement fields to express them according to eigenmodes, and
a statistical analysis of the fields expressed according to the eigenmodes.
A stator assembly including plural stator vanes distributed around an axis of revolution of the stator assembly, a chord of the stator vane, taken at a root of the stator vane, not overlapping, in the direction of the axis of revolution, a chord of an adjacent stator vane, taken at a root of the adjacent stator vane, and a chord of the stator vane, taken at a tip of the stator vane, overlapping, in the direction of the axis of revolution, a chord of the adjacent stator vane, taken at a tip of the adjacent stator vane.
A plate heat exchanger, in particular for an aircraft turbo machine, between a first fluid and a second fluid, the first fluid being intended to circulate in a first direction and the second fluid being intended to circulate in a second direction different from the first direction, the heat exchanger having stacked stages for circulation of the first fluid, and profiled elements at the inlet and outlet of the stages, the profiled elements having a sawtooth-shaped cross-section and defining channels converging at the inlet of the stages and diverging at the outlet of the stages.
F02C 7/14 - Cooling of plants of fluids in the plant
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
SAFRAN LANDING SYSTEMS UK LIMITED (United Kingdom)
Inventor
Bennett, Ian
Abstract
An aircraft landing gear shock absorber strut (50) comprising: an outer cylinder (52) defining an oleo chamber (O) for containing pressurised oleo-pneumatic shock absorber fluid; a sliding tube (52) including a piston head (56) movably mounted within the outer cylinder (52) so as to be movable along an axis of the outer cylinder bore between: a compressed position and an extended position; an annulus portion of the bore defined between the outer cylinder and the sliding tube which varies in length as the sliding tube moves between the compressed position and extended position; an out-stop member (60) located within the annulus portion such that the piston head (56) contacts the out-stop member (60) as the sliding tube (54) moves from the compressed condition to the extended condition to limit extension of the shock absorber strut (50), wherein the out- stop member (60) comprises a resilient portion (72) configured to be resiliently compressed in the axial direction of the outer cylinder (52) by at least 2mm by the oleo- pneumatic force provided by the oleo-pneumatic shock absorber fluid.
SAFRAN LANDING SYSTEMS UK LIMITED (United Kingdom)
Inventor
Bennett, Ian
Abstract
An aircraft landing gear shock absorber strut (50) comprising: an outer cylinder (52) and a sliding tube (54) being movably mounted within the outer cylinder so as to be movable between a compressed position and an extended position, further comprising a first piston head (56) including a first axial surface upon which pressurised oleo-pneumatic shock absorber fluid within an oleo chamber acts to force the sliding tube to move from the compressed position to the extended position; a second piston head (60) slidably mounted within the sliding tube bore; a piston restraining arrangement (62) configured to limit axial separation between the second piston and the outer cylinder; and a first abutment (68) within the sliding tube bore on the opposite side of the second piston head with respect to the oleo chamber, the first abutment being spaced from the second piston head by a first distance when the second piston head is in the first position and the sliding tube is in the extended position, the first abutment being arranged to engage the second piston head as the sliding tube moves from the extended position to the compressed position.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/48 - Arrangements for providing different damping effects at different parts of the stroke
B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
21.
METHOD AND LINE FOR MANUFACTURING A PANEL WITH MULTIPLE ACOUSTIC ELEMENTS FOR AN ACOUSTIC ATTENUATION STRUCTURE
A method for continuously manufacturing a complex acoustic multi-element panel for an acoustic attenuation structure, the method including supplying a thermoplastic resin film at the entry of a stamping system including at least one pair of complementary cylinders, a heating of the thermoplastic resin film upstream of the entry of the stamping system, and a passage of the thermoplastic resin film between the at least one pair of complementary cylinders, the pair of complementary cylinders including a male cylinder with teeth radially protruding from the cylinder and a female cylinder with cavities on its radial surface, the cavities of the female cylinder being of shapes complementary to the shapes of the teeth of the male cylinder and a separation of the stamped film at the exit of the stamping system using a separator disposed at the exit of the stamping system between the stamped film and the female cylinder.
B32B 3/28 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
22.
FUEL CONDITIONING SYSTEM AND METHOD CONFIGURED TO POWER AN AIRCRAFT TURBINE ENGINE USING FUEL FROM A CRYOGENIC TANK
Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger (31) configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air stream (A), and at least one heating turbomachine (2) configured to supply an air flow (A) to the first heat exchanger (31), the heating turbomachine (2) comprising an air intake compressor (21), a combustion chamber (24) and an air exhaust turbine (22) configured to drive the air intake compressor (21), the combustion chamber (24) being supplied with air taken from the air flow (A) and with the fuel (Q) from the fuel circuit (CQ).
SAFRAN LANDING SYSTEMS UK LIMITED (United Kingdom)
Inventor
Bennett, Ian
Abstract
An aircraft landing gear assembly comprising an oleo-pneumatic shock absorber (50) comprising an outer cylinder (52) and sliding tube (54) movable between a compressed position and an extended position, further comprising a sprung element coupled to the shock absorber, movable between a spaced position and an engaged position, and further comprising a weight-on-wheels sensor (62, 64, 66) arranged to monitor movement of the sprung element from the spaced position to the engaged position.
A method includes for each of the portions of a guide of the actuator, obtaining an operating signal measured when a movable element of the actuator travels over the guide portion in question, upon each of a plurality of successive activations of the actuator; for each of the guide portions, seeking wear of the actuator from the operating signals obtained for this guide portion; and locating the wear on the guide or on the motor according to the guide portions from which the wear has been found.
Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
A device comprising: a stand; a frame rotatably mounted relative to the stand; a control arm rotatably mounted on the frame; a roll spider rotatably mounted on the frame; a pitch spider rotatably mounted on the control arm; a roll motor that is stationary relative to the frame and that includes a roll pin rotatably mounted on the roll spider; and a pitch motor that is stationary relative to the frame and that includes a pitch pin rotatably mounted on the pitch spider. A rotary connection device.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
The invention relates to a method for manufacturing a vane (11) of a turbine engine comprising a pressure-face wall (14) and a suction-face wall (15) spaced apart from one another, this vane (11) comprising a tip (S) with:
a bottom wall (18) extending from the pressure-face wall (14) to the suction-face wall (15), each of which comprises a free edge (19, 21) extending beyond this bottom wall (18) to delimit, together with this bottom wall (18), a squealer shape (B);
a partition wall (22) extending from the pressure-face wall (14) to the suction-face wall (15) and spaced apart from the bottom wall (18) to delimit, together with this bottom wall (18), a cavity (C) under the squealer tip;
the method including:
a moulding step to form at least the pressure-face wall (14), the suction-face wall (15) and the partition wall (22);
—a step of forming the bottom wall (18) using an additive manufacturing method by adding metal material.
This method for stopping at least one aircraft turbogenerator (1) comprises: —controlling the stopping (E1) of the turbogenerator (1); —passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); —controlling the extinction of the combustion chamber (6) of the gas turbine (2); —maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, —controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).
A power transmission system for an aircraft turbine engine including a speed reducer including a ring gear that is able to rotate about an axis X, formed from half-rings having annular flanges clamped together by first fastener. The reducer includes an annular channel for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges, this channel being formed by an axial assembly of at least two parts and forming a fairing for the flanges and the first fastener intended to limit aerodynamic disturbances.
A casting ring having a first section made of a heat-conductive material and a second section made of a MAX phase alloy material, and a method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in the casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L1, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L2, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10−4 m/s in the drawing direction.
A method for determining an efficiency fault of at least one module of a turboshaft engine of an aircraft. The method comprising a step of determining an estimated real mapping, a step of determining real indicators from the estimated real mapping, a step of determining a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations, a step of determining simulated indicators for each simulated mapping, a step of training a mathematical model by coupling the simulated indicators with efficiency configurations, and a step of applying said mathematical model to the real indicators so as to deduce therefrom a real efficiency configuration.
B64F 5/60 - Testing or inspecting aircraft components or systems
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
32.
COUNTERCURRENT HEAT EXCHANGER FOR A TURBOMACHINE, TURBOMACHINE, AND METHOD FOR MANUFACTURING THE EXCHANGER
A counter-current heat exchanger for a turbomachine comprising a first and a second circuit, the first and the second circuit being respectively configured to receive a first gas flow and a second gas flow, each circuit including a secondary inlet manifold, an exchanging part and a secondary outlet manifold; the exchanging parts of the first circuit and of the second circuit being delimited by exchange walls configured to direct the first and the second gas flow along a first direction; and wherein the secondary inlet manifold and the secondary outlet manifold of the first circuit extend along a second direction substantially perpendicular to the first direction, and open onto a same face of the exchanger.
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F28D 1/047 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or mo with the heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being bent, e.g. in a serpentine or zig-zag
A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root (1), c) is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.
B22D 19/04 - Casting in, on, or around, objects which form part of the product for joining parts
B22D 19/14 - Casting in, on, or around, objects which form part of the product the objects being filamentary or particulate in form
B22D 19/02 - Casting in, on, or around, objects which form part of the product for making reinforced articles
B33Y 80/00 - Products made by additive manufacturing
C22C 47/08 - Making alloys containing metallic or non-metallic fibres or filaments by contacting the fibres or filaments with molten metal, e.g. by infiltrating the fibres or filaments placed in a mould
C22C 47/06 - Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
D03D 1/00 - Woven fabrics designed to make specified articles
D03D 15/242 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
34.
METHOD FOR MANUFACTURING A BLADE FOR A TURBOMACHINE
A method for manufacturing a blade for a turbine engine, including a root connected to a vane extending in a longitudinal direction, includes providing an assembly having a first part intended to form a root of the blade and a projecting second part projecting in the longitudinal direction from the first part; providing a mold comprising a first impression and a second impression delimiting together a cavity, said cavity comprising a first space and a second space; arranging the first part in the first space of the cavity and the second part in the second space of the cavity; and forming a third part by injecting an aluminium-based alloy in the cavity.
ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS (ENSAM) (France)
SAFRAN (France)
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
CONSERVATOIRE NATIONAL DES ARTS ET METIERS (France)
Inventor
Theze, Alexis
Guinault, Alain
Regnier, Gilles
Abstract
The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).
A method for manufacturing a conductor of a winding of a coil, includes manufacturing a heat-sink preform including a phase-change material, depositing a conductive element by layer deposition of electrically conductive material on the heat-sink preform, including inserting the heat-sink preform into an electrolytic solution of the electrically conductive material, and; electrodeposition for depositing the electrically conductive material on the heat-sink preform.
H02K 3/22 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors consisting of hollow conductors
H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
37.
METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PART HAVING A CELLULAR STRUCTURE AND CORRESPONDING PART
A method for manufacturing a composite material part having a cellular structure that includes at least one cell delimited by walls. The method includes supplying at least a first core, providing a web of a first fibrous reinforcement comprising a plurality of long discontinuous fibers randomly distributed in a plane, and producing at least one strip of the first fibrous reinforcement. The method further includes producing a second fibrous reinforcement in the shape of a sock, inserting the first core into the sock, draping the strip around the sock containing the first core, placing the sock containing the first core and the wrapped strip in a mold, and thermocompression.
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
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
F02K 1/54 - Nozzles having means for reversing jet thrust
38.
INSTRUMENTATION COMB FOR AN AIRCRAFT ENGINE WITH SENSORS AND INTEGRATED ELECTRONIC SYSTEM
Instrumentation comb for an aircraft engine including a central tube with a longitudinal axis on which a determined number of orifices spaced apart along this longitudinal axis are drilled and a base forming a proximal end of this tube and intended to be fixed on a crankcase portion of the aircraft engine, each orifice being associated with a sensor for measuring a physical parameter of the aircraft engine and the base integrates a slave processing unit connected to each of the measuring sensors by a communication link able to receive in real time digital measurement data corresponding to the physical parameters measured by the measuring sensors and intended to be communicated to a master processing unit by a single communication link.
The invention relates to a heat exchanger comprising a support wall and a first plurality of fins that each stand proud from an outer surface of the support wall and are designed to have a first air flow pass over them. According to the invention, the heat exchanger comprises, downstream of the first plurality of fins, a second plurality of fins that each stand proud from the outer surface of the support wall, the first and second pluralities of fins being separated by distribution means which are configured in such a way that the first air flow flows outside the second plurality of fins and a second air flow flowing outside the first plurality of fins passes through the second plurality of fins.
A nickel-based superalloy part includes a nickel-based superalloy substrate, and a metal sublayer covering the substrate, wherein the metal sublayer includes a first and a second layer, the first layer being located between the substrate and the second layer, the first layer including a first γ′-Ni3Al phase and a second γ-Ni phase, the second layer including a first γ′-Ni3Al phase, a second γ-Ni phase and a third β-NiAl phase, the average atomic fraction of aluminum in the second layer being strictly greater than the average atomic fraction of aluminum in the first layer.
In the field of determining the three-dimensional profile of a surface, a system and a method for determining such a three-dimensional profile use a plenoptic camera and a structured lighting system. The method includes: acquiring a sequence of plenoptic images, each formed by a set of pixels each associated with a light intensity of an imaged surface element, and including a plurality of sub-images of the surface from different viewing angles, projecting onto the surface a sequence of structured images synchronised with the sequence of plenoptic images illumating each imaged surface element by a succession of light intensities different from the successions of light intensities which illuminate the other imaged surface elements, constructing, for each pixel of the plenoptic image, an intensity vector representing the succession of light intensities, and pairing each pixel of a sub-image with a pixel of another sub-image depending on a similarity of the intensity vectors.
A method for protecting coils from excessive heating in an aircraft electrical machine comprising a stator (12) and a rotor (14) configured to be rotationally driven with respect to one another, the stator including a plurality of notches (120) receiving one and the same plurality or otherwise of coils, the method including the following successive steps:
inserting an electrical insulator (16) into the notches or onto the teeth of the stator,
installing the coils (18) in the notches or on the teeth of the stator, casting a phase change material (20) in the notches or on the teeth equipped with the coils, the electrical insulator forming a casting mold.
H02K 15/12 - Impregnating, heating or drying of windings, stators, rotors or machines
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
43.
PROTECTION AGAINST OXIDATION OR CORROSION OF A HOLLOW PART MADE OF A SUPERALLOY
A protection method protects at least one hollow internal area of a turbine engine part made of a superalloy from oxidation and/or corrosion, wherein the at least one hollow inner area has been formed by means of at least one core made of a ceramic material limited by an external surface that surrounds it. Before bringing the superalloy around the core made of a ceramic material, the external surface is coated with a material that includes a nanometric layer of hafnium (Hf), and/or a micrometric layer of platinum (Pt), or
A protection method protects at least one hollow internal area of a turbine engine part made of a superalloy from oxidation and/or corrosion, wherein the at least one hollow inner area has been formed by means of at least one core made of a ceramic material limited by an external surface that surrounds it. Before bringing the superalloy around the core made of a ceramic material, the external surface is coated with a material that includes a nanometric layer of hafnium (Hf), and/or a micrometric layer of platinum (Pt), or
a mixture at least of hafnium and platinum.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C23F 11/18 - Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent in other liquids using inorganic inhibitors
44.
LASER HEATING FOR THE MANUFACTURE OR REPAIR OF A TURBINE BLADE
A device for laser heating of a mechanical part of the turbine blade or turbine blade element type, including: one or more laser emitters, for respectively emitting at least a first laser radiation at a first predetermined power towards a first target area of the part and for emitting a second laser radiation at a second predetermined power towards a second target area of the part, different from the first target area, the second predetermined power being different from the first predetermined power.
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 include 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 coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
46.
ACTIVE BALANCING OF MULTIPLE INTERLEAVED PIEZO PUMPS
The present invention relates to a drive circuit for a plurality of piezo-actuated hydraulic pumps for an aircraft, and a hydraulic pump system implementing the same. The drive circuit comprises a voltage boost stage that receives a DC input supply voltage and delivers an increased DC output voltage to a high voltage, HV, link point; a plurality of inverter stages coupled in parallel at the HV link point that receive DC voltage from the HV link point and generate an oscillating output voltage for driving a respective piezo-actuated pump; and a control system that controls the output voltage and phase of the inverter stages to drive the plurality of piezo-actuated pumps out of phase. The control system measures the power consumption of each piezo-actuated pump and regulates the output voltage of at least one of the inverter stages to balance the power consumption of each piezo-actuated pump.
AUTOTRANSFORMER, AUTOTRANSFORMER-RECTIFIER UNIT AND METHOD FOR CONNECTING A PIECE OF ELECTRICAL EQUIPMENT TO A THREE-PHASE GRID BY MEANS OF AN AUTOTRANSFORMER-RECTIFIER UNIT
A three-phase autotransformer including three output groups and three inputs each connected to each of the outputs of a respective output group by windings, the windings being configured so that, when each input has a respective input voltage applied thereto, the three input voltages having the same input amplitude, being 120° out of phase with each other and defining a neutral point: for each output group, a main output voltage, taken between a main output of said output group and the neutral point, has an amplitude greater than the input amplitude; and output voltages of the autotransformer belong to a same Reuleaux polygon, each output voltage being associated with a respective output and being equal to a voltage between said output and the neutral point.
H02M 5/14 - Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases without intermediate conversion into dc by static converters using transformers for conversion between circuits of different phase number
H01F 30/12 - Two-phase, three-phase or polyphase transformers
48.
METHOD FOR AUTOMATIC QUALITY INSPECTION OF AN AERONAUTICAL PART
A method for automatic quality inspection of an aeronautical part, includes detecting faults on an image of the aeronautical part using a trained artificial neural network; training an auto-encoder on a database, by projecting each image of the database onto a small mathematical space in which the images follow a predefined probability law; for each image of the database, calculating a plurality of metrics; supervised training of a classifier from the calculated metrics; detecting faults or anomalies in the image of the aeronautical part using the auto-encoder and the classifier.
Electrical power supply circuit for a power module comprising an electrical transformer, a first substrate having a first side including a heat sink and a second side, a second substrate having a first side including a heat sink and a second side, first metal tracks disposed on the second side of the first substrate, second metal tracks disposed on the second side of the second substrate, electrical connectors disposed between the first and second substrates to electrically connect a first metal track to a second metal track, the primary circuit of the electrical transformer comprising a first part of the first metal tracks and a first part of the second metal tracks, and the secondary circuit of the electrical transformer comprising a second part of the first metal tracks and a second part of the second metal tracks.
The invention relates to a gantry crane (30) and to the associated method of erection, the gantry crane (30) comprising: - a frame (40) comprising at least three first members (32); - a longitudinal rail (50) supported by the frame (40); and - at least three second members (34) extending between opposite first end (34a) and second end (34b) portions, each second member (34) being connected to the frame (40) by means (48) of rigid connection of the second member to the frame and of continuous rotational movement of the second member relative to the frame between a first position in which the second member (34) makes an angle of less than 90° with the first plane (XY) and a second position in which the second member (34) is substantially perpendicular to said first plane (XY).
A method for evaluating the state of an aircraft engine for a given flight, each flight of the aircraft being associated with one time-domain series, includes, each time maintenance of the aircraft is performed, creating a dataset including the time-domain series associated with each flight carried out between the maintenance and the preceding maintenance; creating a set of datasets including each created dataset and dividing it into a training set and a validating set; conjointly training an embedding function and a classifier, selecting a reference time-domain series from a time-domain series of the validating set; and computing a distance between the embedment associated with the time-domain series of the given flight and the embedment of the reference time-domain series, with a view to computing an indicator of engine state.
A method for measuring temperature and deformation of a part or structure on the basis of a single line of optical fiber having a single Bragg rating is provided. The method includes: interrogating the optical fiber based on two sampling frequencies; one being a low frequency and the other being a high frequency, said low frequency being suitable for sensing a slow rate of change corresponding to the temperature variation, and said high frequency being suitable for sensing a fast rate of change corresponding to vibrations; implementing an algorithmic block based on a blind-source-separation (BSS) technique, comprising a frequency analysis, a multivariate analysis and higher-order statistics; and returning to the time domain via an inverse Fourier transform.
G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis
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
53.
ACOUSTIC PANEL AND ASSOCIATED MANUFACTURING METHOD
An acoustic panel has two substantially parallel skins between which cavities forming Helmholtz resonators are arranged. One of the skins is bored with orifices, each of which opens into one of said cavities and forms a neck of the resonators. One or more of said cavities includes of a hollow structure having the shape of a triangular-based prism.
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially 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
B33Y 80/00 - Products made by additive manufacturing
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
09 - Scientific and electric apparatus and instruments
14 - Precious metals and their alloys; jewelry; time-keeping instruments
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Appareils et instruments scientifiques non à usage médical, nautiques, géodésiques, photographiques, cinématographiques, optiques, de pesage, de mesurage, de signalisation, de contrôle (inspection), de secours (sauvetage) et d'enseignement; appareils et instruments pour la conduite, la distribution, la transformation, l'accumulation, le réglage ou la commande de courant électrique; appareils pour l'enregistrement, la transmission, la reproduction du son, des images ou des données; supports d'enregistrement magnétiques, disques acoustiques; appareils et instruments pour la lecture d'enregistrements; équipement pour le traitement des données et ordinateurs; logiciels, périphériques adaptés pour utilisation avec des ordinateurs; terminaux de données; logiciels de gestion de données; programmes de stockage de données; interfaces d'ordinateurs; moniteurs [programmes d'ordinateurs]; serveurs informatiques; serveurs en nuage; lecteurs [équipements de traitement de données]; systèmes électroniques de défense, à savoir: radars en communication militaire, contre-mesures, systèmes de combats électroniques; appareils et instruments de signalisation et de sauvetage, appareils de localisation sonore; balises de détresse maritimes, aériennes et terrestres; radiobalises; balises de direction; balises lumineuses; récepteurs pour signaux de balises; bouées de sauvetage; bouées de signalisation; bouées de repérage; ceintures de sauvetage; gilets de sauvetage; capsules de sauvetage pour situations de catastrophes naturelles; appareils, équipements et instruments électroniques, électroniques et numériques pour la navigation, le guidage, le pilotage, la stabilisation, la localisation, le positionnement de véhicules aériens, terrestres, maritimes et spatiaux; dispositifs de navigation, de guidage, de traçage, de balisage et de cartographie; appareils et systèmes de navigation par satellite; logiciel interactif pour ordinateur fournissant des informations de navigation et de voyage; appareils et instruments électroniques de traçage; appareils électriques et électroniques de détermination de la localisation des destinations; dispositifs pour la localisation du personnel; appareils de repérage de véhicules; appareils pour systèmes de repérage universel [GPS]; émetteurs et récepteurs pour les systèmes de repérage universel [GPS]; logiciels informatiques pour systèmes de localisation mondiaux; logiciels pour systèmes de navigation GPS; boîtes noires [enregistreurs de données]; appareils d'intercommunication; appareils de communication par satellite; satellites; satellites d'intercommunication; processeurs satellites; stations terrestres pour satellites; logiciels pour systèmes de navigation par satellite; antennes de réception pour émissions par satellite; antennes; installations électriques pour la commande à distance d'opérations industrielles; appareils de téléguidage; émetteur [télécommunication]; émetteurs satellite; émetteurs de signaux électroniques; transmetteurs de signaux d'urgence; transpondeurs; émetteurs-récepteurs; récepteurs satellite et radar; systèmes de radar; appareils émetteurs et récepteurs pour transmission à longue distance; moniteurs [matériel informatique]; appareils de télésurveillance; émetteurs pour télécommandes; interfaces audio; alarmes et équipement d'alerte; instruments d'alarme; systèmes de surveillance à alarme; émetteurs et récepteurs de signaux d'alarme; détecteurs d'alarme; unités centrales d'alarmes; sonars; appareils et machines de sondage; appareils électriques de mesure; appareils de mesure de précision; appareils pour mesurer, réguler et enregistrer la distance, le temps, la vitesse, la température, les images et les sons; appareils électriques de régulation; appareils de chronométrage; appareils électroniques de commande de synchronisation; instruments de mesure temporelle (sans inclure les horloges et montres); appareils pour la régulation du temps; appareils et instruments pour l'enregistrement de temps; appareils pour codes temporels; modulateurs et indicateurs de fréquences; appareils à haute fréquence; appareils de surveillance autres qu'à usage médical.
(2) Horlogerie et instruments chronométriques; horloges atomiques; horloges atomiques utilisées dans les systèmes de défense et de sécurité notamment défense par satellites, avions, missiles, sous-marins; horloges mères; oscillateurs d'horloges. (1) Services de télécommunications; information en matière de télécommunication; communications par terminaux d'ordinateurs ou par réseau de fibres optiques; communications radiophoniques ou téléphoniques; services de radiotéléphonie mobile; fourniture d'accès à un réseau informatique mondial; raccordement par télécommunication à un réseau informatique mondial; services de télécommunications interactives; transmission de données en flux continu [streaming]; transfert de données par télécommunication; transmission de données à distance par le biais de télécommunications; télécommunication, y compris services de communication par satellites; transmission par satellite; mise à disposition d'infrastructures de télécommunication; location d'équipements et d'appareil de télécommunication; fourniture de capacité satellitaire [télécommunications]; services d'assistance, d'information et de conseil dans le domaine des télécommunications; services de conseils professionnels en matière de télécommunications.
(2) Évaluations, estimations et recherches effectuées par des ingénieurs dans les domaines scientifiques et technologiques; recherche et développement de nouveaux produits pour des tiers; conduite d'études de projets techniques; conception, développement, installation, maintenance, mise à jour et location de logiciels; programmation informatique; conversion de données et de programmes informatiques autre que conversion physique; services d'analyses et de recherches industrielles; conception de produits; génie des télécommunications; services d'assistance technique (conseils) dans les domaines des télécommunications; services de conseils en technologies des télécommunications; conception et développement de systèmes et réseaux de télécommunications; tests, analyses et contrôles de signaux de télécommunication; programmation de logiciels de télécommunication; logiciel-service [SaaS]; conception de systèmes informatiques; hébergement de serveurs; services de conseils en matière de logiciels; services de programmation informatique pour l'analyse de données; programmation d'équipements pour le traitement de données; services d'analyse de données techniques; services de récupération de données; stockage électronique de données; conseil en ingénierie en matière de traitement de données; services de conseillers en matière de sécurité des données; conseils en technologie de l'information; services de cartographie [géographie]; service d'expert conseil dans le domaine de la navigation par satellite (GNSS); service de recherche et développement dans le domaine de la navigation par satellite et la transmission de radio fréquences; service de développement, configuration, optimisation et installation de logiciels de simulation pour systèmes liés à la géolocalisation.
09 - Scientific and electric apparatus and instruments
14 - Precious metals and their alloys; jewelry; time-keeping instruments
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific (not for medical use), nautical, surveying, photographic, cinematographic, optical, weighing, measuring, signaling, checking (inspecting), life-saving and teaching apparatus and instruments; apparatus and instruments for conducting, switching, transforming, accumulating, regulating or controlling electricity; apparatus for the recording, transmission or reproduction of sound, images or data; magnetic recording media, sound recording disks; apparatus and instruments for reading recordings; data processing equipment and computers; software, peripherals adapted for use with computers; data terminals; data management software; data storage programs; computer interfaces; monitors [computer programs]; computer servers; cloud servers; readers [data processing equipment]; electronic defense systems, namely,: radars in military communication, counter measures, electronic combat systems; signaling and life-saving apparatus and instruments, sound locating apparatus; marine, air and land distress beacons; radio beacons; steering beacons; luminous beacons; receivers for beacon signals; life buoys; signaling buoys; marking buoys; life belts; life jackets; life-saving capsules for natural disasters; electronic, electronic and digital apparatus, equipment and instruments for navigation, guidance, piloting, stabilization, location, positioning of air, land, sea and space vehicles; navigation, guidance, tracking, targeting and map making devices; satellite navigation apparatus and systems; interactive software for computers providing information on navigation and travel; electronic apparatus and instruments for tracking; electric and electronic apparatus for determining the location of destinations; devices for personnel tracking; vehicle tracking apparatus; Global Positioning System [GPS] apparatus; transmitters and receivers for global positioning systems [GPS]; computer software for global positioning systems; software for GPS navigation systems; black boxes [data recorders]; intercommunication apparatus; satellite communication apparatus; satellites; intercommunication satellites; satellite processors; earth stations for satellites; software for satellite navigation systems; receiving antennas for satellite broadcasts; antennas; electric installations for the remote control of industrial operations; remote control apparatus; transmitter [telecommunication]; satellite transmitters; transmitters of electronic signals; emergency signal transmitters; transponders; transceivers; radar and satellite receivers; radar systems; transmitters and receivers for transmitting long-distance; monitors [computer hardware]; remote monitoring apparatus; remote control transmitters; audio interfaces; alarms and alarm equipment; alarms; alarm monitoring systems; alarm signal transmitters and receivers; alarm sensors; central alarm units; sonars; sounding apparatus and machines; electric measuring apparatus; precision measuring apparatus; apparatus for measuring, regulating and recording distance, time, speed, temperature, images and sounds; electric regulating apparatus; timing apparatus; electronic timing control apparatus; time-measuring instruments (not including clocks and watches); apparatus for controlling time; apparatus and instruments for time recording; time code apparatus; frequency indicators and modulators; high-frequency apparatus; monitoring apparatus other than for medical use Timepieces and chronometric instruments; atomic clocks; atomic clocks used in defense and security systems including defense by satellites, airplanes, missiles, submarines; control clocks; oscillators for clocks Telecommunication services; telecommunication information; communications by computer terminals or by fiber-optic networks; communications by radio or telephone; mobile radiotelephony services; providing access to a global computer network; connection via telecommunication to a global computer network; interactive telecommunication services; data streaming; transfer of data by telecommunication; remote transmission of data via telecommunications; telecommunication, including satellite communication services; satellite transmission; provision of telecommunication infrastructures; rental of telecommunication equipment and apparatus; providing satellite capacity [telecommunications]; assistance, information and consulting services in the field of telecommunications; professional consulting services relating to telecommunications Evaluations, estimates and research carried out by engineers in scientific and technological fields; research and development of new products for third parties; conducting of technical project studies; design, development, installation, maintenance, updating or rental of software; computer programming; conversion of computer programs and data, other than physical conversion; industrial analysis and research services; product design; telecommunications engineering; technical assistance services (advice) in the field of telecommunications; telecommunication technology consultancy services; design and development of telecommunication systems and networks; testing, analysis and monitoring of telecommunication signals; programming of telecommunication software; Software as a Service [SaaS]; computer system design; server hosting; software consulting services; computer programming services for data analysis; equipment programming for data processing; technical data analysis services; data recovery services; electronic data storage; engineering consultancy with respect to data processing; consultant services with respect to data security; advice regarding information technology; mapping services [geography]; expert consulting services in the field of satellite navigation (GNSS); research and development in the field of satellite navigation and radio frequency transmission; development, configuration, optimization and installation of simulation software for systems linked to geolocation
A system for heating cryogenic fuel includes a storage take, a supply line, a closed circuit, a cryogenic fuel heat exchanger, one or more working fluid heat exchangers, and a controller The storage tank stores the cryogenic fuel in a liquid state. The supply line connects the storage tank to a combustion chamber of an aircraft turbine engine. The closed circuit circulates a heat-transfer fluid. The cryogenic fuel heat exchanger heats the cryogenic fuel by the heat-transfer fluid. The closed circuit includes a pump for circulating the heat-transfer fluid and a closed expansion vessel connected to the closed circuit. The controller controls the pump to ensure a heat-transfer fluid flow rate inside the closed circuit so that the closed expansion vessel keeps the heat-transfer fluid circulating in the closed circuit at a pressure such that the heat-transfer fluid remains in the liquid state and does not change phase.
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 7/141 - Cooling of plants of fluids in the plant of working fluid
A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.
H02P 7/343 - Arrangements for regulating or controlling the speed or torque of electric DC motors for regulating or controlling an individual dc dynamo-electric motor by varying field or armature current by master control with auxiliary power using Ward-Leonard arrangements in which both generator and motor fields are controlled
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
B60L 53/24 - Using the vehicle's propulsion converter for charging
58.
Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method
A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/20 - 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
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
F02C 9/40 - Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
F02C 9/36 - Control of fuel supply characterised by returning of fuel to sump
59.
Method of characterizing a woven fibrous structure
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQU (France)
ECOLE NORMALE SUPERIEURE PARIS-SACLAYE (France)
Inventor
Schneider-Die-Gross, Julien Paul
Belhaj Saad, Intisar
Mendoza Quispe, Arturo
Parra, Estelle Marie Laure
Roux, Stéphane
Abstract
The invention relates to a method for characterizing, from a volume image, a fibrous structure having a three-dimensional weaving between a plurality of warp yarns extending along a first direction and a plurality of weft yarns extending along a second direction perpendicular to the first one, the method comprising: a first processing of the volume image by filtering along a third direction perpendicular to the first and second directions so as to attenuate the periodic patterns along the third direction, obtaining a two-dimensional image corresponding to an intermediate plane along the third direction of the filtered volume image, a second processing of the two-dimensional image by filtering along the first or second direction so as to attenuate the periodic patterns, obtaining a one-dimensional profile representing the positions of warp or weft columns and corresponding to an intermediate line along the first or second direction.
Device for manufacturing a part using a method of selective fusion or selective sintering on a powder bed comprising a build plate having a working surface, parallel to a first direction and to a second direction, on which surface the part is intended to be manufactured, a wiper which is placed on the working surface and capable of moving and spreading the powder in the first direction on the working surface, characterized in that it further includes at least two acoustic sensors which are fixed and spaced in the second direction on the wiper and capable of detecting an acoustic signal; a laser range finder pointing in the first direction and capable of determining a position of the wiper in the first direction; and a control system capable of detecting an anomaly on the basis of said acoustic signal and of determining a position of the anomaly.
An installation for supplying a cryogenic fuel to a combustion chamber of a turbine engine of an aircraft including a tank, a mixing chamber, and one or more heat exchangers. The tank stores cryogenic fuel in a and connects to a combustion chamber for supplying the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The one or more heat exchangers are provided between the cryogenic fuel and air of an air-conditioning circuit of the aircraft, mounted in a line connecting the tank for cryogenic fuel to the mixing chamber and in a line to be connected to the air-conditioning circuit of the aircraft, the heat exchange taking place therein so as to cool the air of the air-conditioning circuit of the aircraft and to increase the temperature of the cryogenic fuel coming from the tank.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/20 - 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
F02C 7/14 - Cooling of plants of fluids in the plant
62.
Cryogenic fuel supply system for a turbine engine combustion chamber
A cryogenic fuel supply system includes a storage tank, a mixing chamber, an auxiliary heating device, a heat exchanger, and flow distribution devices, and a controller. The storage tank stores cryogenic fuel in a liquid state. The mixing chamber receives various flows of cryogenic fuel in a supercritical or gaseous state, the mixing chamber being connected to a combustion chamber to supply the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The auxiliary heating device heats the cryogenic fuel. The heat exchanger assembly includes a cryogenic fuel/oil heat exchanger and a heat exchanger between the cryogenic fuel and the air circulating in a primary duct of the turbine engine. A flow distribution device is upstream of the auxiliary heating device, and one or more flow distribution devices are disposed upstream of the heat exchanger assembly. The controller controls opening and closing of the flow distribution devices.
A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
B29C 45/16 - Making multilayered or multicoloured articles
F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
B29C 64/147 - Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
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
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 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
64.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
Disclosed is an axial turbomachine (2) that comprises: a first splitter (10) capable of separating an incoming airflow (F) into a radially internal airflow (F') and a radially external airflow, referred to as secondary flow (F2); a second splitter (14) capable of separating the radially internal airflow into a primary flow (F1) and a tertiary flow (F3), said tertiary flow being in a tertiary stream (16) radially external to said primary flow; an air-to-oil heat exchanger (18) placed in the tertiary stream and including surfaces exchanging heat with the air and oil passages extending into said tertiary stream; and structural arms (60) extending radially through the tertiary stream. The axial turbomachine (2) is characterised in that each structural arm has, in the tertiary stream, a cross-section with a downstream portion (62) the width of which decreases downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
Heat exchanger (2) of the air-oil type, for an annular air channel in a turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces for heat exchange with air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and contained in a plane perpendicular to the air flow, the profile of the heat exchange zone being in the form of a circular arc such that it can be placed in the annular air channel. The heat exchanger is characterised in that it comprises an oil inlet (18) and an oil outlet (20) on a radially inner (14') or radially outer (16') face of the heat exchange zone, the oil passages comprising several paths (22) between the oil inlet and oil outlet, distributed along the circular arc profile of the heat exchange zone.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
66.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
The invention relates to an axial turbomachine (2), comprising: a first splitter (10) able to separate an incoming air flow (F) into a radially internal air flow (F') and into a radially external air flow, termed secondary flow (F2); a second splitter (14) able to separate the radially internal air flow into a primary flow (F1) and into a tertiary flow (F3) in a tertiary flow duct (16) radially to the outside of the primary flow; and a heat exchanger (18) arranged in the tertiary flow duct; characterized in that the heat exchanger extends radially and axially in an upstream portion (20) of the tertiary flow duct, having a divergent longitudinal section, the tertiary flow duct comprising a downstream portion (22) having a convergent longitudinal section, along the tertiary flow.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
67.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
Axial turbomachine, comprising: a first splitter nose which can split an incoming air flow into a radially inner air flow and a radially outer air flow, referred to as the secondary flow; a second splitter nose which can split the radially inner air flow into a primary flow and a tertiary flow (F3), the tertiary flow being in a tertiary flow channel (16) radially external to the primary flow and delimited by an inner wall (13) and an outer wall (11); and a heat exchanger (18) of the air-oil type, disposed in the tertiary flow channel. The turbomachine is characterised in that the heat exchanger comprises several angular sectors (38), each angular sector comprising an oil inlet (48) on the inner wall at an angular end of said sector, and an oil outlet (50) on the inner wall at an opposite angular end of said sector.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
68.
AIR-OIL HEAT EXCHANGER COMPRISING A BYPASS FOR A TURBOMACHINE
Heat exchanger (2) for an annular air channel in an axial turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces (6) forming a heat exchange passage for air, said heat exchange zone being radially delimited by an upper wall (12) and a lower wall (9), the oil passages extending radially and axially between said upper and lower walls, said heat exchange zone having a profile facing the air flow and contained in a plane perpendicular to the air flow, and the profile of the heat exchange zone being in the form of a circular arc such that it can be placed in the annular air channel. The heat exchanger is characterised in that it further comprises a wall (8) having a circular arc profile and being parallel to, and radially away from, the heat exchange zone so as to form a bypass passage (10) for the air, parallel to the heat exchange passage, between said wall and the heat exchange zone.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
69.
DEVICE FOR MEASURING AN OPERATING VARIABLE OF A TYRE
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
Inventor
Destraves, Julien
Fagot-Revurat, Lionel
Bailly, Éric
Canu, Antoine
Vera, David
Abstract
The invention relates to a device for measuring an operating variable, to be fitted onto a tyre, comprising:
an electronic circuit distributed over a first face of an electronic board and comprising a sensor;
a protective housing at least partially covering the electronic circuit; and
at least one first antenna wire having one end galvanically connected to the electronic circuit and integrally extending so as to project laterally from the housing;
The invention relates to a device for measuring an operating variable, to be fitted onto a tyre, comprising:
an electronic circuit distributed over a first face of an electronic board and comprising a sensor;
a protective housing at least partially covering the electronic circuit; and
at least one first antenna wire having one end galvanically connected to the electronic circuit and integrally extending so as to project laterally from the housing;
According to the invention, the housing comprises a lateral portion which projects substantially tangentially to a proximal end portion of the first wire in accordance with the generatrix of said first wire.
B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
B29D 30/00 - Producing pneumatic or solid tyres or parts thereof
G01L 17/00 - Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies
G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
G01L 19/06 - Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
G01L 19/08 - Means for indicating or recording, e.g. for remote indication
G01L 9/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles
H01Q 9/28 - Conical, cylindrical, cage, strip, gauze or like elements having an extended radiating surface; Elements comprising two conical surfaces having collinear axes and adjacent apices and fed by two-conductor transmission lines
70.
DEVICE FOR REGULATING THE PRESSURE OF AN AIRCRAFT CRYOGENIC FUEL TANK
A pressure regulating device includes an on-board storage tank, a mixing chamber, first and second lines, a recirculation line, a pressure sensor and a controller. The storage tank stores and supplies cryogenic fuel to a combustion chamber and includes a booster pump. The first line supplies cryogenic fuel in the liquid state and includes a pressurizing pump and a first regulation valve. The second line supplies cryogenic fuel in the gaseous state and includes a compressor and a first control valve. The recirculation line includes a second regulation valve and with a first heat exchanger. The pressure sensor detects the pressure inside the storage tank. The controller receives the pressure and controls the first and second regulation valves, the first control valve, the pressurizing pump, the booster pump and the compressor, as a function of a value of a setpoint pressure inside the storage tank.
A variable frequency generator (VFG) may include a housing, a shaft, a rotor, and a stator with slots. The VFG also includes a first set of stator windings including a first subset of windings and a second subset of windings and a second set of stator windings including a first subset of windings and a second subset of windings. The windings of the first subset of the first set of stator windings are co-located with the windings of the first subset of the second set of stator windings so as to share a common slot of the plurality of slots of the stator. Further, the windings of the second subset of the first set of stator windings are co-located with the windings of the second subset of the second set of stator windings so as to share a common alternative slot of the plurality of slots of the stator.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
ECOLE SUPERIEURE DE PHYSIQUE ET DE CHIMIE INDUSTRIELLE DE LA VILLE DE PARIS (France)
Inventor
Brutt, Cecile
Gerardin, Benoit
Aubry, Alexandre
Derode, Arnaud
Prada, Claire
Abstract
A device, for non-destructive testing of a mechanical part made of a polycrystalline material, includes: an ultrasonic probe including a two-dimensional array of transducers capable of emitting and receiving signals at different excitation angles; and a processing module suitable for controlling the emission and the reception of the transducers, for processing the signals received by the transducers so as to express the signals received by the ultrasonic probe in two planar wave planes constructed from the emission and reception wave vectors of the probe, and for deducing therefrom information representative of the three-dimensional orientation of the fiber structure of the mechanical part.
A device for detecting particles in a lubricating oil of a machine, comprising a particle separator; at least one particle detector; a bypass conduit for the particle-concentrating oil, fluidly connected to an oil outlet of the particle separator, concentrating the particles; and wherein the at least one particle detector is operatively mounted on the bypass conduit so as to be able to detect particles in the bypass conduit.
A method determines the angular setting (β_2) of an annular row of stator vanes arranged downstream of a pusher propeller of a propulsion system with a longitudinal axis. The annular row of stator vanes receives an air flow having a velocity (V2) including a longitudinal component (Viz) and a tangential component (V_iθ) associated with the velocity of gyration generated by the pusher propeller. The method includes the steps of establishing a theoretical model of the pusher propeller using a power (P1) and a mechanical speed (N1) associated with said pusher propeller, and flight conditions that include a velocity of the airflow incident on the pusher propeller, the altitude of said propulsion system and ambient temperature. The method further includes the step of determining an angular setting (β_1) of the pusher propeller from the theoretical model.
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
Inventor
Canu, Antoine
Bailly, Eric
Vera, David
Neba, Eric-Carin
Arnoux, Michaël
Abstract
A pressure measuring device for a tyre includes an electronic circuit distributed over a first face and a second face of an electronic board and comprising a pressure sensor mounted on the first face of said electronic board; an antenna connected to the electronic circuit; a first housing part covering the first face such that together they delimit a first volume, and comprising channels fluidically connecting the first volume to the outside; a second housing part covering the second face such that together they delimit a second volume, and having a base for resting against an inner surface of a tread of the tyre, the second housing part being arranged such that the antenna projects laterally with respect to said second housing part and the housing has a centre of gravity located in the second volume spaced apart from the electronic board.
A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.
Disclosed is a rotating electrical machine with axial air gap, comprising two rotors, each provided with superconducting axial magnetic flux barrier elements around an axis of rotation and having, between them, axial magnetic flux passage areas, at least one armature, comprising windings and a superconducting field coil surrounding the elements and the armature and capable of inducing an axial magnetic field. Each armature is positioned between two of the rotors. The superconducting elements of the rotors are coaxial with one another and also the flux passage areas. A first annular cryogenic enclosure encloses the field coil and a second cryogenic enclosure encloses the two rotors and the armature or only one rotor, with a third cryogenic enclosure around the other rotor without the armature.
H02K 55/04 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type with rotating field windings
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
78.
METHOD FOR CONTROLLING A RECTIFIER CONNECTED TO A PERMANENT-MAGNET SYNCHRONOUS ELECTRIC GENERATOR TO PROVIDE A DIRECT VOLTAGE, CORRESPONDING DEVICE AND COMPUTER PROGRAM
This method comprises: determining a first setpoint (Iq_ref) for a first vector component (Iq) of the phase currents (Ia, Ib, Ic) along a first axis (q) of a rotating reference frame (R) connected to a rotor (112) of the electric generator (108), and a second setpoint (Id_ref) for a second vector component (Id) of the phase currents (Ia, Ib, Ic) along a second axis (d) of the rotating reference frame (R), this second vector component (Id) of the phase currents (Ia, Ib, Ic) being intended to bring about defluxing of the rotor (112); and controlling the rectifier (118) on the basis of the first and second setpoints (Iq_ref, Id_ref) for the vector components (Iq, Id) of the phase currents (Ia, Ib, Ic). The first setpoint (Iq_ref) for the first vector component (Iq) of the phase currents (Ia, Ib, Ic) is determined on the basis of an external feedback loop designed to feedback-control a voltage on a DC bus or to regulate a current from a battery connected to the DC bus.
A turbomachine part or assembly of parts includes a first blade and a second blade, and platform from which the first blade and the second blade extend, The platform has, between a pressure side of the first blade and a suction side of the second blade a non-axisymmetric surface defining at least one fin, and a transverse section of the fin is asymmetric. The transverse section includes a first and a second oblique faces joining at a dorsal edge, the first oblique face is oriented toward the pressure side of the first blade, the second oblique face is oriented toward the suction side of the second blade, and the first oblique face has a steeper slope than the second oblique face.
A method for the non-destructive inspection of an aeronautical component having a step of obtaining a plurality of digital images of a unit area of the aeronautical component, a step of estimating a characteristic image representative of the unit area, each pixel of the characteristic image having a characteristic vector, a step of dividing the characteristic image into a plurality of micro prediction zones, a step of comparing the characteristic vector of each pixel in each micro prediction zone with a previously estimated local statistical model of the micro prediction zone, the local model of a micro prediction zone being obtained by means of a learning algorithm from characteristic vectors of pixels in a micro learning zone of the annotated characteristic image which includes the micro prediction zone.
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
SAFRAN (France)
SAFRAN ELECTRONICS & DEFENSE (France)
SAFRAN LANDING SYSTEMS (France)
Inventor
Neba, Eric Carin
Abstract
The invention relates to a method and a system for determining the temperature in a mounted aircraft tyre. The system is characterized in that it comprises two temperature sensors installed inside the tyre.
A method for manufacturing an acoustic attenuation structure including a complex acoustic multi-element panel extending along a horizontal and a vertical direction and an acoustic skin covering one of horizontal faces of the complex acoustic multi-element panel, the complex acoustic multi-element panel including complex acoustic elements each having a shape gradually narrowing between a base and a tip and partitions surrounding each complex acoustic element to form a plurality of acoustic cells, the partitions extending along the vertical direction from the base of the complex acoustic elements, the complex acoustic multi-element panel being produced by injection of a filled or unfilled thermoplastic or thermosetting material. The complex acoustic multi-element panel and the plurality of partitions are produced as a single part by injection of a filled or unfilled thermoplastic or thermosetting material.
B29C 45/56 - Means for plasticising or homogenising the moulding material or forcing it into the mould using mould parts movable during or after injection, e.g. injection-compression moulding
The invention relates to a method for mounting an axle (12) in a bore (14) of a bogie (16) mounted on an aircraft landing gear (18), the landing gear (18) being in a gear-down position, the bore (14) extending in a substantially horizontal direction referred to as the axle installation direction, between a first open end (14a) and a second open end, the method comprising: a) supplying a mobile bearing structure (30) comprising means for moving the axle (12) which are able to move in a direction substantially parallel to the axle installation direction, b) installing the axle (12) on the means for moving the axle, c) aligning the axis (C) of the axle (12) with the axis (B) of the bore (14), d) introducing the axle (12) into the bore (14) of the bogie (16) by moving the means for moving the axle (12) in the direction substantially parallel to the axle installation direction.
An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.
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
85.
METHOD FOR MAKING A METAL PART WITH A COMPLEX GEOMETRY WITH A THIN WALL
A metal part with a wall thickness less than 5 mm includes a preform made from a flexible composite sheet, a flexible composite sheet segment, and an appended insert including a fastening portion that is sandwiched between a rear end of the preform and the flexible composite sheet segment. The flexible composite sheet segment encloses the fastening portion of the appended insert.
A method for skeletonizing the strands of a composite material part in a 3D image having a step of detecting oriented section centers of the strands and a link from each center to the closest center having the same orientation, the detection being carried out by means of at least one reference volume having an oriented centered strand pattern, the detection step having, for each reference volume: • a step of determining portions of the image, • a step of calculating a correlation score between the reference volume and each portion associated with the central voxel of each portion, so as to obtain a correlation score for each voxel of the image; and • a step of determining the strand centers corresponding to the voxels having a correlation score which corresponds to a local maximum.
An x-ray tomographic method for reconstructing an object, includes, on the basis of a plurality of images, each image in the plurality of images corresponding to a projection of the object, reconstructing the object using an iterative reconstruction method so as to produce a plurality of reconstructions x(m) of the object.
A method for manufacturing a part of nitrided steel includes a step of nitriding the part. After nitriding, laser shocking is carried out on a surface of the nitrided part.
The invention relates to a method for controlling a turbomachine comprising a gas generator, the turbomachine comprising an electric machine forming a device for injecting torque into/removing torque from one of the low pressure/high pressure rotation shafts of said gas generator. Said method comprises a step of implementing a fuel control loop in order to determine a fuel flow setpoint into the combustion chamber, and comprising, in the event that at least one operability limit is reached, determining a corrected fuel flow setpoint, said corrected fuel flow setpoint exhibiting a difference in relation to the setpoint. Said method also comprises a step of implementing a torque control loop in order to determine a torque setpoint for the electric machine, and comprising determining a torque correction quantity as a function of said difference, said torque setpoint being determined as a function of said torque correction quantity.
The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.
A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.
D03D 25/00 - Woven fabrics not otherwise provided for
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A system for locating a strand including fibers of a first woven preform material, the preform including, at the surface, strands of fibers of a second material and the strand including fibers of the first material forming a tracer. The system further includes a camera; a light source emitting a non-polarized incident beam configured to be directed towards the preform; a polarizer configured to polarize the non-polarized incident beam before interacting with the preform in order to obtain a polarized incident beam; and a crossed analyzer; the first material being chosen from among glass, aramid and aluminum oxide; the second material being chosen from among carbon and silicon carbide; the camera being configured to film a reflected beam originating from the interaction of the polarized incident beam with the preform, the reflected beam having previously crossed the crossed analyzer, so as to locate the tracer of the preform.
G02B 27/28 - Optical systems or apparatus not provided for by any of the groups , for polarising
B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
93.
OIL DEAERATOR DEVICE WITH RESERVOIR PROVIDED WITH A STABILIZING WALL
The invention relates to an oil deaerator device (2) for a turbomachine lubricating system, comprising a reservoir (4) comprising an internal volume (10) with a bottom (10.1), an oil outlet (18) on the bottom (10.1), and an oil inlet opposite to the bottom (10.1); an oil deaerator (6) arranged at the oil inlet of the reservoir (4); and a stabilizing wall (14) arranged in the internal volume (10) opposite the bottom (10.1) and provided with at least one passage (14.1) for the oil so as to delimit a stabilized buffer oil volume (12).
ASSOCIATION POUR LA RECHERCHE ET LE DEVELOPPMENT DES METHODES ET PROCESSUS INDUSTRIELS (France)
Inventor
Chauchat, Paul
Barrau, Axel
Bonnabel, Silvère
Abstract
The present invention relates to a navigation assistance method for a mobile carrier (1) comprising an inertial navigation unit (10) comprising at least one inertial sensor (12), in which, over a determined observation window, the following steps are implemented by an estimation unit (11) of the inertial navigation unit (10): (E10) parametrisation of a non-linear system configured to estimate a navigation state of the mobile carrier (1) over a given time interval at an iteration n as a function of a kinematic model and/or measurements acquired by at least one inertial sensor (12); (E20) linearisation of the system so that the system expresses a navigation state at iteration n as a function of the state at iteration n−1 and a correction to this navigation state, said system being initialised by a first a priori state; (E21) estimating, by a Kalman filter and stochastic cloning, a first correction of a navigation state at iteration n; (E22) estimating a second correction of the navigation state at iteration n by an information filter operating in reverse and stochastic cloning; (E30) determining a third correction by merging the first and second corrections; and (E40) correcting the navigation state at iteration n as a function of the third correction, the corrected state being used at iteration n+1.
G01C 21/16 - Navigation; Navigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
95.
MACHINERY FOR WINDING A FIBROUS TEXTURED MATERIAL, AND ASSOCIATED WINDING METHOD
The present invention relates to machinery (10) for winding a fibrous textured material (12, 120, 220) about a support (14, 140, 240), allowing the gradual modification of the shape of the support as the winding progresses, and comprising compaction devices (20,329) for the purpose of reducing the wrinkling of the textured material obtained after compaction.
SAFRAN LANDING SYSTEMS UK LIMITED (United Kingdom)
Inventor
Bennett, Ian Robert
Abstract
An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly, the linkage assembly comprising: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point the such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, though an axis or plane bisecting the apex pivot point and the second control link pivot point.
An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.
An aircraft landing gear assembly comprising: a structural pin defining a first bore having a longitudinal insertion axis; a cap for covering the bore, the cap comprising: a base portion; a head portion; a body portion positioned between the base portion and the head portion; and a bolt which extends between the head portion and the base portion and comprises a threaded portion so that engagement of either the head portion or the base portion with the threaded portion moves either the head portion or the base portion relative to the other, the body being formed of an elastically deformable material such that upon tightening of the bolt, the base portion moves towards the head portion and the elastically deformable material moves radially outwards such that a contact surface of the elastically deformable material engages with an inner surface of the first bore in order to retain the cap.
SAFRAN LANDING SYSTEMS UK LIMITED (United Kingdom)
Inventor
Bennett, Ian Robert
Abstract
An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly, the linkage assembly comprising: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point the such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, though an axis or plane bisecting the apex pivot point and the second control link pivot point.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE LA ROCHELLE (France)
Inventor
Delautre, Joel
Audic, Christophe Philippe
Hamadi, Sarah
Jaquet, Virginie
Pedraza Diaz, Fernando
Pasquet, Annie
Abstract
A turbomachine part includes a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities.
