Abstract

Method for the manufacture of at least one skin (12), in particular of an acoustic panel (10) for an aeronautical engine, comprising the laying of a thermoplastic material (TP) on a surface (S) of a lay-up tool (200) via a depositing tool (100) configured to exert a pressure on the thermoplastic material (TP) and to heat the latter while it is being laid, wherein the lay-up tool (200) comprises a thermal regulation device configured to locally heat the surface (S) of the lay-up tool (200).

IPC Classes  ?

• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 33/02 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with incorporated heating or cooling means
• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns

Abstract

The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises a gas turbine engine (200) and at least one electric machine (300, 400) which is mechanically coupled to a rotating shaft (210, 220) of the gas turbine engine (200) so as to be rotated for generating electricity. In this control method, a mechanical power take-off setpoint by the electric machine (300, 400) is changed when an operating parameter of the gas turbine engine (200) reaches a predetermined limit. The invention also relates to a control unit (500) adapted to perform this method, a motor assembly (100) incorporating this control unit (100), the electric machine (300, 400) and the gas turbine engine (200), and a computer program for performing this method.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F02C 9/00 - Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 6/14 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads

Abstract

The present invention relates to an electrical system (4) for an aircraft (100), comprising: a first bus (411); a second bus (412); a first generator (401); a first converter (421); a second generator (402); and a second converter (422).

IPC Classes  ?

• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

Method for locating a mark (46, 48) on a casing (10) of a turbomachine (1) of an aircraft, characterized in that it comprises: a) a step of visually inspecting the arms (16), the outer surface (12a) of the internal shroud (12) and the inner surface (14a) of the external shroud (14), and, in the event that at least one mark (46, 48) is detected at step a), b) a step of manually mounting a visual inspection device (32) around the inner end (16a) or outer end (16b) of one or more of the arms (16), and c) a step of determining the location of the at least one mark (46, 48) in a zone (Z1, Z2, Z3) of the casing (10).

IPC Classes  ?

• F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 21/10 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to unwanted deposits on blades, in working-fluid conduits, or the like
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F04D 29/00 - NON-POSITIVE-DISPLACEMENT PUMPS - Details, component parts, or accessories
• G01N 21/88 - Investigating the presence of flaws, defects or contamination

Abstract

The invention relates to a method for maintaining a bladed wheel of a high-pressure turbine of a turbomachine, extending along an axis, comprising a disc (11) comprising cavities (15), and blades (12) extending radially and each comprising an airfoil and a radially inner root (14), the root (14) of each blade (12) being mounted in a cavity (15) of the disc (11), the root (14) bearing on the disc (11) via surfaces of the root (14) and of the disc (11) which form bearing surfaces (19), characterized in that at least one foil (21) is mounted removably between the root (14) of at least one blade (12) and the disc (11), at the corresponding bearing surfaces (19), the method comprising the following steps: measuring a radial clearance between the tip of at least one blade (12), that is to say the radially outer end of the blade (12), and a casing of the turbomachine situated facing the bladed wheel, and, if the radial clearance is greater than a predetermined value, removing the foil (21).

IPC Classes  ?

• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
• F01D 5/30 - Fixing blades to rotors; Blade roots

Abstract

The method for manufacturing a blade (32) of a turbomachine (100) comprises: - manufacturing a part (4) comprising an air flow path zone (10) and a layer (20) covering the zone, the layer having cavities (21) forming a periodic pattern, the manufacture taking place by injecting a mixture comprising a binder and a powder; - removing a larger part of the binder from the part; - sintering the part; and - removing the layer (20) from the part to obtain the blade (32).

IPC Classes  ?

• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor for producing castings from a slip
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 3/10 - Sintering only

Abstract

The present invention relates to an aircraft part comprising: a composite material structure comprising a fibrous reinforcement embedded in a matrix; a heating element (9) configured to heat the part, the heating element (9) being embedded in the matrix of the composite material structure.

IPC Classes  ?

• B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
• B64C 11/26 - Fabricated blades
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The present invention relates to a nickel-based superalloy, characterized in that its composition comprises or advantageously consists essentially of, in percent by weight of the total composition: Al 2.5 - 3.8, Co 7.9 - 16.9, Cr 9.7 - 13.1, Mo 2.6 - 4.1, Nb 0 - 0.41, Ta 0 - 1.9, Ti 4.4 - 6.4, W 1.9 - 4.2, B 0.010 - 0.030, C 0.010 - 0.040, Hf 0.20 - 0.40, Zr 0.040 - 0.070, the remainder being Ni together with unavoidable impurities. The invention also relates to the powder of a superalloy according to the invention, to the method for manufacturing parts made of superalloy according to the invention, and to the parts that can be obtained by this method.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• B22F 3/00 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor
• B22F 3/17 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor by forging
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 7/00 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting
• B22F 3/24 - After-treatment of workpieces or articles
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F04D 29/02 - Selection of particular materials
• B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy

Abstract

The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises at least a first electric machine (300) and a gas turbine engine (200). The gas turbine engine (200) comprises a low-pressure shaft (210) and a high-pressure shaft (220). The electric machine (300) is coupled to the low-pressure shaft (210), and the control method comprises a step, in which a mechanical work take-off is controlled to the first electric machine (300) for braking a rotation of the low-pressure shaft (210) in response to an activation of a thrust reverser (281) of the gas turbine engine (200) and/or to a disturbance of the airflow in a transverse plane at an air intake of the gas turbine engine (200). The invention also relates to a control unit (500) adapted to perform this method, a motor assembly (100) incorporating this control unit (100), the electric machine (300) and the gas turbine engine (200), and a computer program for carrying out this method.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing

Abstract

The invention relates to a system for measuring the fatigue (11) of a mechanical structure (10), comprising: - a first force sensor (19.1) capable of generating a first signal (S1) representative of a force applied to a first mechanical part (13) of the mechanical structure (10); - a second force sensor (19.2) capable of generating a second signal (S2) representative of a force applied to a second mechanical part (14) of the mechanical structure (10); and - an electronic processing module (21) configured to calculate a correlation coefficient (Corr(S1, S2)) between the first signal (S1) and the second signal (S2), and to indicate a state of fatigue of the mechanical structure (10) as a function of a temporal change in the previously calculated correlation coefficient (Corr(S1, S2)).

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G01M 99/00 - Subject matter not provided for in other groups of this subclass
• B60N 2/00 - Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
• B64D 11/06 - Arrangements or adaptations of seats
• B64D 25/00 - Emergency apparatus or devices, not otherwise provided for
• B60N 2/90 - Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles - Details or parts not otherwise provided for

Abstract

The invention relates to an aeronautical propulsion unit (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), wherein the annular row of downstream stator blades (16) comprises at least one downstream stator blade of a first type (16a), each downstream stator blade (16a) of the first type being located around the longitudinal axis (X) in a first angular sector (S1) about the longitudinal axis, each downstream stator blade of the first type (16a) being of a fixed pitch, and at least one downstream stator blade of a second type (16b), each downstream stator blade of the second type (16b) being located around the longitudinal axis (X) outside said first angular sector (S1), each downstream stator blade of the second type (16b) being of a variable pitch.

IPC Classes  ?

• B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
• B64C 11/30 - Blade pitch-changing mechanisms
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• B64D 27/14 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, fuselage
• F02C 7/20 - Mounting or supporting of plant; Accommodating heat expansion or creep
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings

Abstract

The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each downstream stator blade (16) being of variable pitch, and wherein at least one of the downstream stator blades (16) is in a fixed-pitch configuration relative to another of the downstream stator blades (16) in that it has a pitch angle (γ) less than the pitch angle (γ) of the other downstream stator blade (16).

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• B64C 11/30 - Blade pitch-changing mechanisms
• B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
• B64D 27/14 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, fuselage
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• B64C 11/00 - Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
• B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
• F02C 9/20 - Control of working fluid flow by adjusting vanes

Abstract

The present invention relates to an electrical distribution route for an aircraft comprising electrical cables (40) and electrical connection interface members (38), the route comprising a diagnostic and detection device for diagnosing and detecting an arc fault. The diagnostic and detection device comprises: an optical fibre (14) laid along the entire distribution route and comprising at least one Bragg grating (20) at each connection interface member (38), an optical reflectometer (36) coupled to an upstream end of the optical fibre (14), and an acquisition central processing unit (34) configured to detect and locate one or more electric arc faults over a connection interface member by comparing the current spectral signature with the reference spectral signature of the optical fibre.

IPC Classes  ?

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

Abstract

j1n1nn) carried out by at least one sensor (Cap1-Capk1n1n1nJJ); - determining (EDP) at least one partial derivative value (DG11-DGn1nn) for the estimation (E0) from the at least one partial derivative value (DG11-DGnn).

IPC Classes  ?

• G01C 21/00 - Navigation; Navigational instruments not provided for in groups
• 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
• G01C 21/28 - Navigation; Navigational instruments not provided for in groups specially adapted for navigation in a road network with correlation of data from several navigational instruments
• G01S 19/45 - Determining position by combining measurements of signals from the satellite radio beacon positioning system with a supplementary measurement
• G01S 19/48 - Determining position by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system
• G05D 1/02 - Control of position or course in two dimensions

Abstract

The invention relates to a nickel-based alloy powder, that comprises in weight percentages, 14.00 to 15.25% of chromium, 14.25 to 15.75% of cobalt, 4.00 to 4.60% of aluminium, 0 to 0.50% of iron, 0 to 0.15% of manganese, 3.00 to 3.70% of titanium, 3.90 to 4.50% of molybdenum, 0 to 0.015% of sulphur, 0 to 0.06% of zirconium, 0.012 to 0.020% of boron, 0 to 0.20% of silicon, 0 to 0.10% of copper, 0 to 150 ppm of carbon, 0 to 0.5 ppm of bismuth, 0 to 5 ppm of lead, 0 to 1000 ppm of platinum, 0 to 1000 ppm of palladium, 0 to 50 ppm of hydrogen, 0 to 5 ppm of silver, 0 to 120 ppm of nitrogen, 0 to 1000 ppm of rhenium, 0 to 410 ppm of oxygen and 0 to 500 ppm of inevitable impurities, the rest being made up of nickel, and has a particle size D10 between 3 and 10 μm, a particle size D90 between 20 and 40 μm and a particle size D50 between 10 and 20 μm, the values of the particle sizes D10, D50 and D90 having been measured by laser diffraction according to standard ISO 13322-2. The invention also relates to a method for manufacturing a part using said powder and a resulting part.

IPC Classes  ?

• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor for producing castings from a slip
• B22F 3/24 - After-treatment of workpieces or articles
• B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• F01D 5/26 - Antivibration means not restricted to blade form or construction or to blade-to-blade connections
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• B22F 1/10 - Metallic powder containing lubricating or binding agents; Metallic powder containing organic material
• B22F 1/148 - Agglomerating
• B22F 3/15 - Hot isostatic pressing
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product

Abstract

The invention relates to a titanium-based alloy powder which comprises, in percentages by weight, 32.0 to 33.5% aluminium, 4.50 to 5.10% niobium, 2.40 to 2.70% chromium, 0 to 0.1% iron, 0 to 0.025% silicon, 0 to 100 ppm carbon, 0 to 100 ppm nitrogen, 0 to 1000 ppm dioxygen, 0 to 50 ppm dihydrogen and 0 to 500 ppm unavoidable impurities, the balance being titanium, and which has a D10 particle size of between 3 and 10 μm, a D90 particle size of between 20 and 40 μm and a D50 particle size of between 10 and 25 μm, the D10, D50 and D90 particle size values having been measured by laser diffraction in accordance with standard ISO 13322-2. The invention also relates to a method for manufacturing a part using this powder and to a part thus obtained.

IPC Classes  ?

• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor for producing castings from a slip
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• C22C 14/00 - Alloys based on titanium
• C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
• C22F 1/18 - High-melting or refractory metals or alloys based thereon
• B22F 3/24 - After-treatment of workpieces or articles
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• B22F 3/15 - Hot isostatic pressing
• B22F 1/10 - Metallic powder containing lubricating or binding agents; Metallic powder containing organic material
• B22F 1/148 - Agglomerating

Abstract

The invention relates to a turbine engine (1) for an aircraft, which turbine engine has a primary annular flow path (10) and a cold stream duct (20, 30) extending around the primary annular flow path (10), said turbine engine comprising: an impeller (22, 32), a compressor (11), a combustion chamber (12), a first turbine (13) including a first turbine rotor (14), a second turbine (17) including a second turbine rotor (18), a first connecting shaft (52) and a second connecting shaft (54), an inter-turbine stator (16) disposed between the first turbine (13) and the second turbine (17), and a first cooling circuit (110) having consecutively: a first cooling inlet (112) located between the impeller (22, 32) and the compressor (11), a first passage (115) extending within the inter-turbine stator (16), and a first cooling outlet (118) extending into the cold stream duct (20, 30).

IPC Classes  ?

• F01D 5/08 - Heating, heat-insulating, or cooling means
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/12 - Cooling
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F02C 7/12 - Cooling of plants
• 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

Abstract

The present invention relates to blading (25, 26) for a turbomachine (10), comprising: - a blade (31) having an aerodynamic profile; - a platform (32, 33) comprising a flow-path surface (321) intended to delimit a primary flow path (21A) of the turbomachine (10), which path is intended, when the turbomachine (10) is in operation, to receive a flow that splits, upstream of the blade (31), into a suction-face flow (EE) and a pressure-face flow (EI); and - an internal canal (34) which has an intake opening (35) and an ejection opening (36), these each opening onto the flow-path surface (321) of the platform (32, 33), the ejection opening (36) opening downstream of the intake opening (35) and the intake opening (35) opening toward the pressure-face flow (EI).

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

One aspect of the invention relates to a method for detecting defects for an aeronautical part, comprising: • Training, during a plurality of epochs, an artificial neural network to supply a defect probability for each pixel of an image, • For each epoch and for each image of a validation set, creating a defect probability matrix based on defect probabilities for each pixel of the image, • For each epoch, determining, for each image of the validation set, based on the defect probability matrices, a curve of defect detection as a function of false alarms, • Determining a set of the N best epochs on the basis of the defect detection curves and of a business criterion, • For each epoch of the N best epochs, inspecting the image to be inspected by applying the artificial neural network with parameters associated with said epoch, so as to obtain an inspected sub-image associated with said training epoch.

IPC Classes  ?

• G06T 7/00 - Image analysis

Abstract

The invention relates to a turbomachine (1) with a low-pressure shaft (8) having an internal passage (18) for a first air stream (A1) and a first segment (8a), a second segment (8b) comprising a first frustoconical portion (8b'), an intermediate lubrication chamber (16) wherein at least one bearing (20c) is arranged, the intermediate lubrication chamber (16) being arranged in an intermediate casing (10), an annular air chamber (25) configured to be supplied with air from a low-pressure compressor (3), the air chamber (25) being at least partly axially delimited by the first frustoconical portion (8b') and a radial separating wall (80a) mounted around the first segment (8a), the first frustoconical portion (8b') further having an opening (19) to enable the first air stream (A1) to pass from the air chamber (25) to the internal passage (18).

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements

Abstract

The present invention relates to a fuel control system (4) comprising: a fuel source; a supply conduit; a main circuit comprising: a first centrifugal pump; a connecting conduit; a second centrifugal pump; a discharge conduit; and a secondary circuit.

IPC Classes  ?

• F02C 7/236 - Fuel delivery systems comprising two or more pumps
• F04D 1/06 - Multi-stage pumps
• F04D 13/14 - Combinations of two or more pumps the pumps being all of centrifugal type

Abstract

The invention relates to an electrically interconnecting member (1) configured to electrically join a printed circuit board (200) belonging to a mechanical part (100) to a piece of electrical equipment (400), the printed circuit board (200) comprising output tracks (300), said electrically interconnecting member (1) comprising: a contact surface configured to be fastened to the mechanical part (100), a free surface (3) opposite the contact surface, input terminals placed on the contact surface and configured to be superposed on the output tracks (300) of the printed circuit board (200), and output interfaces (7) placed on the free surface (3) at distance from the input terminals and configured to be connected to the piece of electrical equipment (400), at least one input terminal comprising a cavity configured to receive a conductive adhesive so as to connect together the input terminal and the output terminal (300) when they are superposed.

IPC Classes  ?

• H05K 1/11 - Printed elements for providing electric connections to or between printed circuits
• H05K 3/32 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits
• H05K 1/09 - Use of materials for the metallic pattern
• H05K 1/14 - Structural association of two or more printed circuits
• H05K 3/36 - Assembling printed circuits with other printed circuits
• H05K 3/10 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern
• H05K 5/00 - Casings, cabinets or drawers for electric apparatus

Abstract

The invention relates to a method for producing a magnet for a rotor of an electric machine, the method comprising a first phase (P1) of producing a magnet blank which comprises a step (ET4) of pressing powders into a magnet mould in the presence of a magnetic field while subjecting the powders to a magnetic field generated by a first magnetisation tool, a step (ET6) of densifying the obtained magnet blank and a second phase (P2) of finishing the magnet blank comprising at least one final magnetisation step in order to obtain a magnet, characterised in that the mould is arranged in a densifying chamber and in that the densifying step (ET6) is carried out by flash SPS sintering in the densifying chamber.

IPC Classes  ?

• H01F 41/02 - Apparatus or processes specially adapted for manufacturing or assembling magnets, inductances or transformers; Apparatus or processes specially adapted for manufacturing materials characterised by their magnetic properties for manufacturing cores, coils or magnets
• H01F 1/08 - Magnets or magnetic bodies characterised by the magnetic materials therefor; Selection of materials for their magnetic properties of inorganic materials characterised by their coercivity of hard-magnetic materials metals or alloys in the form of particles, e.g. powder pressed, sintered, or bound together

Abstract

The present invention relates to a method for manufacturing an instrumented strand (1), intended for a textile operation for forming a fibrous preform of a part made of composite material. The method comprises: • unreeling at least one wire-based detection element (5) which is able to transmit a physical signal, with reinforcing wires (104; 108) being attached around said at least one unreeling wire-based detection element so as to form a preform (110) of the instrumented strand; and • depositing a retaining binder (111) on the instrumented strand preform obtained in this way, so as to obtain the instrumented strand.

IPC Classes  ?

• B29B 15/12 - Coating or impregnating of reinforcements of indefinite length
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• D02G 3/36 - Cored or coated yarns or threads
• D02G 3/44 - Yarns or threads characterised by the purpose for which they are designed
• D03D 1/00 - Woven fabrics designed to make specified articles
• D03D 15/267 - Glass
• D03D 15/275 - Carbon fibres
• D03D 15/47 - 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 structure of the yarns or threads multicomponent, e.g. blended yarns or threads
• D03D 15/547 - 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 properties of the yarns or threads with optical functions other than colour, e.g. comprising light-emitting fibres
• D03D 25/00 - Woven fabrics not otherwise provided for
• 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
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings

Abstract

The invention relates to a system for attaching a turbomachine blade, comprising: - a blade comprising, at the blade root, two portions (54, 56) that are separated from one another in a transverse direction X so as to provide a cavity (C) therebetween extending downwards in the direction Y from the top of the blade, from a cavity bottom (Cl) to a cavity opening (C2) on the outside, located at the lower end of the blade root, - an element (60) for attaching the blade partially engaged inside the cavity with the engaged portion having a shape, in a plane defined by the directions X and Y, which extends towards the bottom (Cl) flaring in the direction X, the two separated portions (54, 56) of the blade root that are in contact with the flared shape of the attachment element (60) having corresponding flared shapes.

IPC Classes  ?

• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• 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 70/24 - 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
• D03D 25/00 - Woven fabrics not otherwise provided for
• D03D 41/00 - WOVEN FABRICS; METHODS OF WEAVING; LOOMS - Details peculiar to these looms

Abstract

The invention relates to a sealing system (21) for a turbomachine bearing enclosure (E1), comprising a stator (22) carrying a rotor (23), this system (21) comprising a seal (25) carried by the stator (22) and surrounding the rotor (23), an external peripheral groove (26) carried by the stator (22) in the vicinity of the seal (25) for collecting oil (H) which exits the enclosure (E1) running along the rotor (23) through the seal (25) and which is centrifuged by the rotor (23) towards this groove (26), and a drain (36) at the bottom for discharging the oil (H) from the groove (26). This groove (26) is open towards the inside and is delimited by a base (33) extended by two side walls (34, 35), the side wall (35) opposite the seal (25) is extended by a skirt (38) oriented obliquely towards the base (33) to delimit a gutter (43) opening towards the base (33). Figure for the abstract: Figure 4

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F16J 15/00 - Sealings
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearings; Lubricating
• F16C 33/66 - Special parts or details in view of lubrication
• F16J 15/16 - Sealings between relatively-moving surfaces
• F16J 15/447 - Labyrinth packings
• F16J 15/54 - Other sealings for rotating shafts
• F16N 31/00 - Means for collecting, retaining, or draining-off lubricant in or on machines or apparatus
• F16J 15/18 - Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings
• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Abstract

The invention relates to a propulsion assembly (1) for an aircraft having at least one propulsion member (10), a gas turbomachine (T) configured to rotate the propulsion member (10), an electric machine (M), mounted downstream of the gas turbomachine (T), having a shaft (Ml) that rotates as one with the gas turbomachine (T), the electric machine (M) being mounted in a chamber (2) supplied with a cooling airflow (FR) from the secondary stream (V2), and at least one system for cooling the electric machine (M), which system is mounted in the chamber (2) and comprises at least one ventilation member (3) configured to be rotated in the chamber (2) by the shaft (M1), and at least one step-up gearing member (6) mounted between the shaft (M1) and the ventilation member (3) configured to rotate the ventilation member (3) at a speed that is different from the speed of the shaft (M1).

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 25/12 - Cooling
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02K 1/04 - Mounting of an exhaust cone in the jet pipe

Abstract

The invention relates to a heating turbomachine (2) for a fuel-conditioning system (SC), which is configured to supply an aircraft turboshaft engine (T) with fuel (Q) from a cryogenic tank (RC), the heating turbomachine (2) comprising: a compressor (21); a turbine (22); a combustion chamber (24) which is configured to discharge a flow of exhaust air (AE) loaded with heat energy and to rotate the turbine (22); at least one fluid circuit (CM) in which a heat-transfer fluid (M) circulates in the downstream direction; and at least one post-combustion heat exchanger (32) which is mounted in the fluid circuit (CM) and is configured to extract heat energy from the exhaust air flow (AE) between the combustion chamber (24) and the turbine (22).

IPC Classes  ?

• F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
• F02C 7/224 - Heating fuel before feeding to the burner
• F02C 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant

Abstract

The invention relates to a method for manufacturing an inter-blade platform (100) of a turbomachine fan (1), the platform (100) comprising a base (110) having first and second sacrificial lateral edges (131, 132) having a thickness which is less than that of the central part (120) of the base (110), the method comprising producing a preform (200) of the platform (100) by three-dimensional weaving, comprising a central part portion (220) and two sacrificial edge portions (231, 232) whose thickness is less than that of the central part portion (220), the difference in thickness between the lateral edge portions (231, 232) and the central part portion (220) being produced by removing a plurality of warp threads situated outside the central part portion (220) and not being woven with weft threads.

IPC Classes  ?

• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• D03D 1/00 - Woven fabrics designed to make specified articles
• D03D 25/00 - Woven fabrics not otherwise provided for
• B29L 31/00 - Other particular articles
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements

Abstract

The present invention relates to an assembly (12) for a turbomachine, comprising: - an outer casing (15) made of half-shells; - an inner casing (14); - a plurality of guide vanes (13) mounted between the outer casing (15) and the inner casing (14), - a structural casing comprising a flange (23) which is radially inside the inner casing (14); and - a system (24) for blocking the inner casing (14) on the structural casing, comprising a generally annular tab (25) fixed to one of the inner casing (14) and the structural casing and a complementary chute (26) fixed to the other of the inner casing (14) and the structural casing, the chute (26) being configured to receive the tab (25) and to block it along the axis (X) with respect to the structural casing.

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/64 - Mounting; Assembling; Disassembling of axial pumps

Abstract

The present invention relates to a turbine rotor (1) comprising a rotor disc (2), provided at its periphery with a plurality of axial cells (23) for receiving a bilobed root (30) of a blade (3), each cell (23) comprising a radially inner cavity (232) and a radially outer cavity (231). This rotor is characterised in that it comprises a ring (4) for axially retaining the blade roots and an annular flange (5), the ring (4) comprising a radially inner portion provided with notches (43) and being arranged against the upstream face (21) of the disc (2), so that each of its notches (43) is located opposite a cell (23) of the disc (2), the flange (5) being secured against the upstream face of the ring (4), forming a space (E) with said disc (2), and comprising at least one air-intake opening (54) which opens into said space (E), and in that each blade (3) comprises a groove (33) for receiving the outer circumferential edge (46) of said ring (4).

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 5/08 - Heating, heat-insulating, or cooling means

Abstract

The present invention relates to an axial-flux superconducting electric machine (1) comprising an inductor (6, 7) and an armature (5), the inductor (6, 7) comprising:• superconducting pads (7) able to move in rotation about an axis (X) of the electric machine (1); and• a superconducting coil (6), centred on the axis (X) and extending radially outside the superconducting pads (7), the superconducting coil (6) being configured to generate a magnetic field. The electric machine (1) additionally furthermore comprises a flux barrier (12) made of a superconducting material and extending between the superconducting pads (7) and the superconducting coil (6), said flux barrier (12) being attached to a circumferential wall (7a) of the superconducting pads (7) so as to move together with the superconducting pads (7).

IPC Classes  ?

• H02K 1/2793 - Rotors axially facing stators
• H02K 21/04 - Windings on magnets for additional excitation
• H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
• H02K 55/06 - Dynamo-electric machines having windings operating at cryogenic temperatures of the homopolar type
• H01F 6/02 - Quenching; Protection arrangements during quenching
• H01F 6/06 - Coils, e.g. winding, insulating, terminating or casing arrangements therefor

Abstract

The invention relates to a method for carrying out tomographic analysis of a composite part comprising a matrix and fibres, the method comprising the following steps: - acquiring at least one two-dimensional image of the part by means of a tomographic device, - generating a plurality of shapes (40) characteristic of the fibres and of convolution masks (50, 51, 52) comprising a plurality of copies of the characteristic shape (40), - computing, for each of the characteristic shapes (40), a product of convolution of the two-dimensional image with the corresponding convolution mask (50, 51, 52), and obtaining a convolution image, - detecting a position corresponding to an overall maximum in all the obtained convolution images and attributing a fibre centre to said position, - marking as processed a region of the image placed around the fibre centre, and - iterating the steps of computing, detecting and marking on the unprocessed regions of the image.

IPC Classes  ?

• G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]

Abstract

The invention relates to a system for controlling a device (1) provided with at least one equipment item (1i), the control system comprising at least one sensor (3) capable of measuring operating quantities of the device, and two specific channels (3ia, 3ib) for measuring a redundant sensor for each equipment item (1i), at least one embedded control means (2a, 2b) configured to determine a command intended for at least one equipment item (1i) as a function of the at least one measurement of the operating quantity of the device (1) and a selected measurement of the controlled equipment item (1i), the control system further comprising a calculating means (5) configured to determine the selected measurement of the at least one controlled equipment item (1i) by means of a Kalman filter observer as a function of the at least one measurement of the operating quantity of the device (1) and the measurements of the two specific channels (3ia, 3ib) for measuring a redundant sensor for the controlled equipment item (1i).

IPC Classes  ?

• G05B 9/03 - Safety arrangements electric with multiple-channel loop, i.e. redundant control systems

Abstract

The invention relates to a method for braking an aircraft turbine engine including a fan (6) or a propeller connected to a turbine (5) by a shaft (7), and an electric generator (9) connected to the shaft (7), the method comprising the following steps: a request to brake the turbine engine by thrust reversal; a calculation of a turbine braking setpoint by a control system (10); and in response to the braking setpoint, an adjustment by the control system (10) of a resistor (11) of a dissipative load (12) to draw electric power from the electric generator (9) to the dissipative load (12).

IPC Classes  ?

• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 9/58 - Control of fuel supply conjointly with another control of the plant with power transmission control with control of a variable-pitch propeller
• F02K 1/66 - Reversing fan flow using reversing fan blades

Abstract

The invention relates to a blade (1) made of a composite material, the blade comprising a fibrous reinforcement densified by an organic matrix and being provided, in an attachment zone (4), with a metal element (5), the blade being characterised in that the reinforcement comprises, in at least one region of the attachment zone, a surface textile orientation adapted to the direction of mechanical stresses by having first skin threads that extend in a main mechanical stress direction (DA) and that are bonded to second skin threads transverse to the first threads, the first skin threads making up most of the surface area of the region of the attachment zone.

IPC Classes  ?

• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 5/14 - Form or construction
• 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 70/24 - 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
• D03D 25/00 - Woven fabrics not otherwise provided for
• D03D 41/00 - WOVEN FABRICS; METHODS OF WEAVING; LOOMS - Details peculiar to these looms

Abstract

The invention relates to a heat exchanger (21) for a turbomachine, in particular an aircraft turbomachine, having a longitudinal axis (X), comprising: a supporting wall (22) extending in a first direction (L); a plurality of fins (23), each of which rises in a second direction (R) from the supporting wall (22) and being intended to be swept by an air stream (F3a, F2), and a profiled panel (27) covering the fins (23) and extending in the first direction between a first diverging-profile wall upstream of the fins and a second converging-profile wall downstream of the fins. According to the invention, the heat exchanger comprises an air intake device (35) configured to slow the air stream in a third direction, the device (35) having multiple separate air intake openings (36) which are arranged upstream of the fins (23) in the first direction (L) and which are distributed in the third direction (C).

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

The invention relates to a vane (4) made of a composite material for an aircraft turbomachine fan, the vane comprising means (8) for measuring internal deformations of the vane and means (9) for remotely storing and transmitting signals for measuring the deformation of the vane, which means are connected to the measuring means, the measuring means and the remote storage and transmission means being located in the composite material.

IPC Classes  ?

• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for

Abstract

The invention relates to a method for controlling a gas turbine engine (1) comprising a body (3, 4) comprising a compressor (31, 41), a turbine (32, 42) and a shaft (33, 43), the turbine being capable of driving the compressor via the shaft, and an electric motor (15) capable of rotating the shaft, comprising the steps of: a) estimating a temperature gradient between a first and a second part of the body, b) comparing the gradient with a threshold, c) if the gradient is less than the threshold, driving the shaft with a speed varying according to a first profile, d) if the gradient is greater than the threshold, controlling the electric motor to drive the shaft so as to vary its speed according to a second profile, such that, when the speed of the shaft is within a critical interval, an acceleration of the shaft is greater than an acceleration according to the first profile within the same critical interval.

IPC Classes  ?

• F01D 25/36 - Turning or inching gear using electric motors
• F01D 19/02 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine casing

Abstract

The invention relates to a method for non-destructive testing of a batch of industrial parts by means of X-ray tomography. This method comprises, for one part from the batch, taken as a calibration part (C), acquiring, with a beam-blocking grid (4) inserted between an X-ray source (1) and the calibration part (C), calibration intensity images at different projection angles, the beam-blocking grid comprising a set of elements (EA) for the attenuation of the X-rays, and, for each projection angle, determining an image of scattered radiation from the calibration intensity image acquired at this projection angle. This method also comprises removing the beam-blocking grid (4) and, for each part in the batch, acquiring raw intensity images at the different projection angles, and correcting, for each projection angle, the raw intensity image acquired at this projection angle by means of the scattered radiation image determined for this projection angle.

IPC Classes  ?

• G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]

Abstract

The invention relates to a method for managing devices installed in a nacelle (1) of a turbine engine (2), the devices being provided with radio tags and the turbine engine (2) being fitted with a radio frequency identification reader (8) and with at least two time-reversal antennae (3), which method comprises the following steps: - mapping the electromagnetic field inside the closed nacelle (1) - matching the known position of the devices with the electromagnetic characteristics of their respective radio tags - carrying out an inventory by time-reversal focusing of waves.

IPC Classes  ?

• G06Q 10/00 - Administration; Management
• B64D 29/00 - Power-plant nacelles, fairings, or cowlings
• B64F 5/60 - Testing or inspecting aircraft components or systems
• H04B 7/06 - Diversity systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
• G06Q 10/20 - Administration of product repair or maintenance

Abstract

Component for a fuel cell or electrolyzer with acid electrolyte which is provided with an anticorrosion coating, and also such a fuel cell or electrolyzer with acid electrolyte, the component comprising an electrically conductive substrate (31), and an anticorrosion coating (32) deposited on at least one surface of the substrate (31), the anticorrosion coating (32) comprising at least one main layer based on tantalum nitride doped using one or more dopants chosen from the family of transition metals or lanthanides.

IPC Classes  ?

• H01M 8/0228 - Composites in the form of layered or coated products
• H01M 8/086 - Phosphoric acid fuel cells [PAFC]
• H01M 8/1018 - Polymeric electrolyte materials
• C25B 9/65 - Means for supplying current; Electrode connections; Electric inter-cell connections
• C25B 11/069 - Electrodes formed of electrocatalysts on a substrate or carrier characterised by the substrate or carrier material consisting of two or more compounds
• C25B 13/04 - Diaphragms; Spacing elements characterised by the material
• H01M 8/10 - Fuel cells with solid electrolytes
• H01M 8/0243 - Composites in the form of mixtures

Abstract

The invention relates to a component for a solid-oxide electrolyte electrolyser or fuel cell provided with an anticorrosion coating, as well as such a solid-oxide electrolyte electrolyser or fuel cell, the component comprising an electrically conductive substrate (31), and an anticorrosion coating (32) deposited on at least one surface of the substrate (31), the anticorrosion coating (32) comprising at least one main tantalum-nitride-based layer doped with one or more doping elements chosen from the family of the transition metals or lanthanides.

IPC Classes  ?

• H01M 8/0228 - Composites in the form of layered or coated products
• C25B 9/65 - Means for supplying current; Electrode connections; Electric inter-cell connections
• C25B 13/07 - Diaphragms; Spacing elements characterised by the material based on inorganic materials based on ceramics
• H01M 8/1246 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides
• H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
• H01M 8/0243 - Composites in the form of mixtures

Abstract

The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a direction (Y). A filler material (41) is located in the cavity (4) at a distance from the opening (5). A reinforcement (6), the density of which is higher than the density of the material (41), comprises a first reinforcement portion (61) located in the cavity (4) against the material (41) and a second reinforcement portion (62) for closing the opening (5) between the portions (21, 31) to form a single piece.

IPC Classes  ?

• B64C 11/22 - Solid blades
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 11/26 - Fabricated blades
• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

Assembly for producing a moulding made of removable material of a turbomachine blade and comprising an injection mould for said removable material in which mould a first core element (22) and a second core element (21) are able to be mounted in a predetermined moulding position, the first and second core elements (21, 22) extending in a first direction (Z), the mould comprising: - a first face (20) for moulding an intrados face of the blade and a second face for moulding an extrados face of the blade and arranged opposite the first face in a second direction (Y) perpendicular to the first direction (Z), - retaining members (P1a, P1f, P2a, P2f, P3a, P3f, P6a, P6f, P6'f) for holding the cores in position in the injection mould, characterized in that the first moulding face (20) comprises at least one first retaining member (P1a, P1f, P2a, P2f, P3a, P3f) extending from the first moulding face (20) in the second direction (Y), said first retaining member (P1a, P1f, P2a, P2f, P3a, P3f) comprising a first bearing point at which it bears against a first bearing surface of a core element (21, 22), the first bearing surface extending against the core element (21, 22), so as to hold said core element in position in the second direction (Y).

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/10 - Cores; Manufacture or installation of cores

Abstract

Assembly for producing a moulding made of removable material of a turbomachine blade and comprising an injection mould for said removable material in which mould a first core element (22) and a second core element (21) are able to be mounted in a predetermined moulding position, the first and second core elements (22, 21) extending in a first direction (Z), the mould comprising: -a first face (20) for moulding an intrados face of the blade and a second face for moulding an extrados face of the blade and arranged facing the first face in a second direction (Y) perpendicular to the first direction (Z), - retaining members (P4, P5) for holding the cores (22, 21) in position in the injection mould, wherein at least a first retaining member (P4, P5) extends from the first face of the mould in the second direction and passes at least partially through the first and second core elements (22, 21), the first retaining member (P4, P5) comprising a first bearing point (P4a, P5a) at which it bears against the first core element (22) and a second bearing point (P4f, P5f) at which it bears against the second core element (21).

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/04 - Use of lost patterns
• B22C 9/22 - Moulds for peculiarly-shaped castings
• B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles
• B22C 23/00 - Tools; Devices not mentioned before for moulding

Abstract

The present invention relates to an application head (1) for automatically applying fibres, which application head comprises at least: - an application roller (3) that is designed to apply fibres to a mould (F), which application roller is rotatably movable on its axis for applying fibres to the mould; and - a feed device (10) comprising a coil of a strip (12) of fibres (16) having a predefined orientation, the strip of fibres being configured to be transferred by unwinding the feed device onto the application roller with at least one portion of the fibres of the strip being oriented such that they are not perpendicular to the axis of the roller.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• F01D 5/30 - Fixing blades to rotors; Blade roots
• B64C 11/04 - Blade mountings

Abstract

lnn nlnn log |Snn || + zn Sn 1ZnSnn ZnYnYn nn and the expected values according to the model and the preceding measurements. The values of the local inconsistency are summed over a group of recursions in an analysis window to generate a quantity referred to as the overall inconsistency. A measurement anomaly is detected on the basis of partial derivatives of the overall inconsistency with respect to the measurements or with respect to uncertainty parameters of the sensors (16, 18) that are given to the Kalman filter (5), within the analysis window.

IPC Classes  ?

• 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
• G06F 11/00 - Error detection; Error correction; Monitoring

Abstract

The invention relates to a method for manufacturing a panel (100) comprising a plurality of partitions (121) defining cells (150) covered by at least one skin (110, 130), the skin (110, 130) being formed by draping fibrous structures (210) impregnated with a thermoplastic material on the upper edges (121a) of the partitions (121) by automatic placement of fibres, the upper edges (121a) of the partitions (121) and the fibrous structures (210) being joined together with the aid of a localized heating device (30) at the moment they are placed in contact, the method being characterized in that the fibrous structures (210) are draped with a draping tension (T) on the interface between each edge (121a) of a partition (121) and the deposited fibrous structure (210) applying a shear stress of between 50% and 80% of the maximum shear stress before rupture of the interface.

IPC Classes  ?

• B29D 24/00 - Producing articles with hollow walls
• B29C 70/56 - Tensioning reinforcements before or during shaping
• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers

Abstract

The invention relates to a turbine engine module, comprising: - a fan (3) intended to be rotated by a fan shaft (32) and comprising a plurality of variable-pitch blades (30); and - a pitch change system comprising a control means (52) connected to the blades via a linking mechanism (51), the control means including a stationary body rigidly connected to the fan shaft (32) and a movable body (54) connected to the linking mechanism (51), the pitch change system comprising an annular part (70) which has one portion rigidly connected to the movable body, which is generally bell-shaped and which extends at least partially radially outwards from the stationary body. According to the invention, the module comprises an annular shroud (80) removably attached to the annular part (70) and comprising means (81) for fastening to the linking mechanism (51).

IPC Classes  ?

• F02C 9/20 - Control of working fluid flow by adjusting vanes
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• F02K 1/66 - Reversing fan flow using reversing fan blades
• F02K 1/76 - Control or regulation of thrust reversers
• B64C 11/06 - Blade mountings for variable-pitch blades
• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic

Abstract

The invention relates to a device (94) for transferring fluid, for a turbine engine (1) having a longitudinal axis X, which device includes a stator part (96) intended to be connected to a stator apparatus (98, 99) of the turbine engine and a rotor part (97) into which the stator part is inserted. According to the invention, the stator apparatus comprises at least one duct (124, 125) fluidly connected to at least one pipe (119, 120) of the stator part, the stator part and the stator apparatus including an attachment interface intended to removably receive attachment members, the attachment interface and the attachment members being configured to cause the pipe and duct (119, 120, 124, 125) to be sealingly coincident, and the transfer device comprising at least one passage (83) which provides an external tool (170) with access, upstream of the transfer device, to the attachment members and extends through the transfer device.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F16H 57/04 - Features relating to lubrication or cooling

Abstract

The invention relates to a tool (30) for moulding a duct for an aircraft turbine engine, the duct being made of a fibre-based composite material and comprising a curved tubular portion, one end of which is connected to a peripheral flange, this tool (30) comprising: - a base (40); - a generally elongate and curved body (50), this body (50) being formed by an assembly of first parts (52) which are fitted tightly together and which include a first central release key (53) which extends from one end of the body (50) to the other and which is configured to be removed first upon release of the body (50). The invention also relates to a method for manufacturing a duct for an aircraft turbine engine using a tool (30) as previously described.

IPC Classes  ?

• B29C 33/48 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
• F04D 19/02 - Multi-stage pumps

Abstract

The invention relates to an aircraft turbomachine subassembly comprising an annular duct (36) which extends concentrically about a longitudinal axis and in which a flow of air flows from upstream to downstream, the annular duct comprising a duct portion (28) which defines a gooseneck having an upstream inlet section and a downstream outlet section. A plurality of radial arms (B1, B2) extend circumferentially in the duct portion (28). One or more intermediate walls (P1, P2) extend between two circumferentially adjacent arms (B1, B2) which form a pair of circumferentially adjacent arms from among the plurality of circumferentially adjacent arms, in such a way as to separate the annular duct portion (28) locally between the two arms of the pair of arms into a radially inner portion (Ci) and a radially outer portion (Ce), the latter being further from the longitudinal axis than is the radially inner portion.

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings

Abstract

The invention relates to an aerodynamic element (28) of a turbomachine comprising a body (32) extending in a radial main direction and a radial end (34, 60) located at a radial end of the body (32), the aerodynamic element (28) further comprising a heat exchanger between an internal fluid of the turbomachine and an airflow flowing around the body (32) of the aerodynamic element (28), characterised in that the heat exchanger has a heat pipe (38) through which a working fluid flows comprising an evaporation portion (40) in which the working fluid exchanges heat with the internal fluid and a condensation portion (42) in which the working fluid exchanges heat with the airflow.

IPC Classes  ?

• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
• F01D 25/12 - Cooling

Abstract

The invention relates to a part (105) comprising a substrate (10) made of ceramic matrix composite material, said substrate being coated with a multilayer stack comprising at least, and in this order, starting from the substrate: - a tie layer (11) comprising silicon; - an insulation layer (12) comprising a rare earth disilicate or silica; - a barrier layer (14) comprising a rare earth disilicate; the part further comprising at least one thermocouple (13) inserted between the insulation layer and the barrier layer.

IPC Classes  ?

• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 41/90 - Coating or impregnating for obtaining at least two superposed coatings having different compositions at least one coating being a metal
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• C04B 41/52 - Multiple coating or impregnating
• G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for

Abstract

The invention relates to a turbomachine module, having: - a fan comprising variable-pitch blades, - a speed reducer (34) connected to a fan shaft guided in rotation by two guide bearings, - a system for changing the pitch of the blades that comprises a control means having an annular body secured to the fan shaft and a movable body, - a fluid-transfer device (103) for supplying the control means, the speed reducer being of the planetary gear train type, the transfer device being upstream of the speed reducer and having a stator part (105) and a rotor part (112) engaged in the stator part, the rotor part being coupled in rotation with the annular body, the control means being arranged upstream of the guide bearings.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

Abstract

The invention relates to a hydraulic control circuit (57) of a dual-action orientation actuator (61) for the orientation of fan blades of a turbojet engine, comprising an oil reservoir (63), a variable-displacement axial piston pump (26) comprising an inclinable plate driven by a control actuator (47) that has a control chamber, and by a compensation actuator (48) that has a compensation chamber, the pump (26) being supplied by the reservoir (63) and having its outlet connected to one of the chambers of the orientation actuator (61), the other chamber of said orientation actuator (61) being connected to the reservoir (63), the control chamber and compensation chamber being pressurized at a pressure corresponding to the outlet pressure of the pump (26), and wherein the control and compensation chambers are arranged to increase the inclination of the plate in order to increase the displacement of the pump (26) when the supply pressure of said chambers increases.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F04B 1/324 - Control of machines or pumps with rotary cylinder blocks by varying the relative positions of a swash plate and a cylinder block by changing the inclination of the swash plate

Abstract

The invention relates to a hydraulic control circuit (57) of a dual-action orientation actuator (61) for the orientation of fan blades of a turbojet engine, comprising an oil reservoir (63), a variable-displacement axial piston pump (26) comprising an inclinable plate driven by a dual-action control and compensation actuator (47) that has a control chamber (53) and a compensation chamber (54), the pump (26) being supplied by the reservoir (63) and having its outlet configured to be able to be connected by a supply line (64) to a second chamber (59) of the orientation actuator (61), a first chamber of said orientation actuator being connected to the reservoir (63), the chambers of the control and compensation actuator (47) both being pressurized at a pressure corresponding to the outlet pressure of the pump (26), and wherein the control and compensation chambers are arranged to increase the inclination of the plate in order to increase the displacement of the pump (26) when the pressurization pressure of said chambers increases.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F04B 1/324 - Control of machines or pumps with rotary cylinder blocks by varying the relative positions of a swash plate and a cylinder block by changing the inclination of the swash plate

Abstract

One aspect of the invention relates to a system for cooling a liquid for lubricating an aircraft turbomachine, comprising an exchanger (213) comprising a cooling volume (201) and a circuit (230) for cooling a heat-transfer fluid by a loop for circulating the two-phase fluid, with thermocapillary pumping. The cooling circuit (230) comprises - a condenser (3) comprising channels (32) connected in parallel to one another in order to make it possible to cool the fluid circulating in the condenser (3) from a vapour state to a liquid state, - a first capillary evaporator (2) of the exchanger (213) in order to absorb the heat of the lubricating liquid in the first volume (201), the first evaporator (2) comprising a capillary porous wick (200) for separating the heat-transfer fluid in the two-phase state between a liquid state and a gaseous state by a capillary pressure jump.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange

Abstract

The invention relates to a method for producing a part (10), in particular a part of composite material (10), in particular for a turbine engine, comprising at least: - a step of producing a preform, during which a fibrous preform (20) intended to form an outer skin (13) of the part is produced; - a step of producing a core, during which a rigid core (30), in particular a hollow rigid core (30), intended to form a framework of the part is produced; - an insertion step, during which the rigid core (30) is inserted into the fibrous preform (20), - an injection step, during which a matrix is injected into the fibrous preform (20); and - a heat-treatment step, during which polymerisation of the matrix is carried out.

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40).

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F02C 9/20 - Control of working fluid flow by adjusting vanes
• F02C 9/52 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
• F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows

Abstract

The invention relates to a method for acquiring and correcting a tomographic reconstruction of an industrial part (4), comprising steps of identifying (34) noisy areas and of replacing (42), in a tomographic reconstruction, the noisy areas with corrected areas simulated on the basis of a theoretical model and a real digital volume made three-dimensionally.

IPC Classes  ?

• G06T 5/00 - Image enhancement or restoration
• G06T 5/50 - Image enhancement or restoration by the use of more than one image, e.g. averaging, subtraction

Abstract

The present document relates to a method for additive manufacturing of a part by successive deposition of layers of powder, within a manufacturing machine (16) comprising a preparation zone (18) for at least one layer and a consolidation zone (20) for the powder, which are offset from one another, said method comprising the following steps: a) preparing at least one layer comprising at least two zones filled with at least two different powders, for example of different materials and/or particle sizes, in said preparation zone (18); b) moving the layer thus prepared into the consolidation zone (20); c) depositing said prepared layer onto a manufacturing support (22) or onto an already consolidated portion of said part; and d) consolidating at least a portion of said layer, for example by sintering or melting, or by adding a binder.

IPC Classes  ?

• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/34 - Process control of powder characteristics, e.g. density, oxidation or flowability
• B22F 12/58 - Means for feeding of material, e.g. heads for changing the material composition, e.g. by mixing
• B22F 12/37 - Rotatable
• B22F 12/55 - Two or more means for feeding material
• B33Y 10/00 - Processes of additive manufacturing
• B22F 12/33 - Platforms or substrates translatory in the deposition plane
• B22F 3/00 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor
• B33Y 70/10 - Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials
• B22F 10/37 - Process control of powder bed aspects, e.g. density
• B22F 12/86 - Serial processing with multiple devices grouped
• B22F 12/00 - Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
• B29C 64/236 - Driving means for motion in a direction within the plane of a layer
• B29C 64/245 - Platforms or substrates
• B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
• B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber

Abstract

The invention relates to a hydraulic assembly (450) for an aircraft engine, the assembly comprising: - a pump (54) comprising a housing (54a) and a rotor (54b) arranged inside the housing (54a), the housing (54a) having at least one hydraulic line (540) for the passage of a fluid; and - a hydraulic transfer unit (56) comprising: a hydraulic transfer block (56a) attached to the housing (54a) and comprising an internal fluid passage channel (67, 68) which communicates with the hydraulic line (540), and a casing (56b) which covers the transfer block (56a) and which is guided in rotation about an axis of revolution (Y) and about the transfer block (56a), the casing (56b) having a fluid outlet port (75, 76) that communicates with the internal channel (67, 68).

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• F04D 29/36 - Blade mountings adjustable
• F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven

Abstract

The present invention relates to a turbine rotor (2) of a turbine engine of an aircraft, the rotor comprising a rotor disc (3) provided at its periphery with a plurality of cavities (30) for receiving the root (42) of a blade (4). This rotor is characterised in that each blade (4) comprises a circumferential coupling rib, in that it comprises a plurality of platforms (5), which comprise a main wall (50) that is extended at its two ends by an upstream radial wall (51) and by a downstream radial wall (52), the two longitudinal edges of each platform comprising a groove (504) for receiving part of said coupling rib of one of the two blades (4) between which this platform (5) is assembled, and in that the height of each upstream radial wall (51) is such that said wall extends radially inwards beyond the bottom of the cavity (30), until it is in front of the upstream face (32) of the rotor disc (3).

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

The invention relates to a heat exchanger (21) for a turbomachine, in particular an aircraft turbomachine, the heat exchanger comprising a support wall (22) extending substantially in a longitudinal direction L, a first plurality of fins (23) each extending in a radial direction R from a radially outer surface (24) of the support wall (22) and intended to have an airflow flow across them, and a profiled panel (25) covering the fins (23) and extending in the longitudinal direction. According to the invention, the heat exchanger comprises a second plurality of fins (26) each extending from a radially outer surface (27) of the panel (25) in a radial direction, the panel (25) extending between the first and second plurality of fins (23, 26).

IPC Classes  ?

• 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
• F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations

Abstract

A method for managing the torque of an aircraft turbomachine comprising a fan (6) or a propeller of variable pitch connected to a turbine (5) by a shaft (7) and a reduction gear (8), and an electric generator (9) connected to the shaft (7), the method comprising the following steps: measuring the torque on the shaft (7) using a torque sensor (10); when the occurrence of a torque peak is measured by the torque sensor (10), calculating a braking setpoint of the turbine (5) by a control system as a function of the measured torque; and, in response to the braking setpoint, adjusting, by the control system, a resistor (11) of a dissipative load (12) for drawing electrical power from the electric generator (9) towards the dissipative load (12).

IPC Classes  ?

• F01D 17/04 - Arrangement of sensing elements responsive to load
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
• B64C 11/06 - Blade mountings for variable-pitch blades

Abstract

The invention relates to an aircraft comprising at least one unducted turbine engine for the propulsion of the aircraft, the turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with respect to the longitudinal axis, each stator blade being defined, in a plane (PT) transverse to the longitudinal axis, by an angular position (θ); and at least one aerodynamic obstruction (OA) positioned close to the turbine engine. The stator of the turbine engine comprises stator blades having a first chord, referred to as conventional blades (51), and at least one stator blade having a second chord larger than the first chord, referred to as the elongate blade (52), said at least one elongate blade (52) being positioned in an interference angular range (PAI) defined opposite the aerodynamic obstacle (OA), so as to increase the straightening of the airflow from the rotor in the interference angular range (PAI).

IPC Classes  ?

• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
• F02C 7/20 - Mounting or supporting of plant; Accommodating heat expansion or creep

Abstract

The invention relates to a turbomachine (10) for an aircraft comprising a stator (16), a turbine shaft (17) and an electric machine (18) arranged to the rear of the turbine shaft, and comprising an electric machine stator (22) and an electric machine rotor (24), a rotationally fixed coupling carriage (19) capable of moving in axial translation relative to the electric machine rotor between coupled and uncoupled positions, coupling members (28, 29) which are designed to engage with one another after the coupling carriage has moved from the uncoupled position to the coupled position and to transmit a torque from the turbine shaft to the electric machine rotor when they are engaged, and an elastic return member (31) designed to elastically return the coupling carriage in axial translation to the coupled position.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

The present invention relates to a nickel-based alloy comprising, in weight percent: - 4.0 to 20.0% cobalt; - 14.0 to 18.5% chromium; - 1.8 to 2.6% aluminium; - 1.3 to 1.9% titanium; - 5.5 to 6.5% tantalum; - 0.01 to 0.10% carbon; - 0.003 to 0.02% boron; and - 0.01 to 0.10% zirconium. The present invention also relates to a method for manufacturing a part made of the nickel-based alloy, the method comprising: - preparing a billet that has the same composition as that of the nickel-based alloy; - shaping the part; and - heat treating the part.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• C22C 1/02 - Making non-ferrous alloys by melting

Abstract

The present invention relates to a nickel-based alloy comprising, in weight percent: - 4.0 to 15.7% cobalt; - 15.3 to 19.5% chromium; - 1.6 to 5.45% molybdenum; - 1.65 to 2.5% aluminium; - 2.8 to 4.3% titanium; - 0.01 to 0.10% carbon; - 0.003 to 0.02% boron; and - 0.01 to 0.10% zirconium. The present invention also relates to a method for manufacturing a part made of the nickel-based alloy, the method comprising: - preparing a billet that has the same composition as that of the nickel-based alloy; - shaping the part; and - heat treating the part.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• C22C 1/02 - Making non-ferrous alloys by melting

Abstract

A fuel distribution assembly (11) for a turbomachine, the distribution assembly (11) extending between a first interface plane (P1) and a second interface plane (P2) substantially parallel to the first interface plane (P1), the distribution assembly (11) comprising a plurality of distribution ducts (13), each duct (13) comprising: - at least one inlet portion (15) opening into the first interface plane (P1) or into the second interface plane (P2), - at least one outlet portion (19) opening into the first interface plane (P1) or into the second interface plane (P2), and - a median portion (17) fluidically connecting each inlet portion (15) of the duct (13) and each outlet portion (19) of the duct (13). The median portion (17) of each duct (13) has an internal cross section (S) of substantially elliptical shape.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems

Abstract

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

IPC Classes  ?

• B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/36 - Process control of energy beam parameters
• B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B33Y 70/00 - Materials specially adapted for additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The invention relates to a method for producing a bladed component (10) for an aircraft turbine engine, this bladed component (10) comprising a blade (12) which has a stacking axis (X) and at least one longitudinal end of which is connected to a transverse platform (14), the method comprising the steps of: a) producing a fibrous preform (18), this preform (18) comprising a first part (16) that is intended to form a blade (12) and at least one second part (20) that is intended to form a platform (14), this second part (20) of the preform (18) comprising a disconnect that defines two stacked portions (22) that are separated by a disconnect surface that is substantially parallel to the axis (X), b) folding the portions (22), respectively, on two opposing sides of the first part (16), and c) stiffening the preform (18).

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/22 - 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
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• 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 5/30 - Fixing blades to rotors; Blade roots

Abstract

The invention relates to an electric machine that comprises a rotor (7), a stator (2), and a vacuum chamber (10), the rotor (7) and/or the stator (2) comprising a superconducting material, the rotor (7) and/or the stator (2) that comprises the superconducting material being placed in the vacuum chamber (10). The electric machine further comprises a cooling system (11), placed in the vacuum chamber (10), for cooling the rotor and/or the stator, and a valve (12) passing through a peripheral wall (13) of the vacuum chamber (10).

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
• H02K 55/04 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type with rotating field windings

Abstract

The invention relates to a tool-electrode for machining a recess in a conductive part by spark machining of the die-sinking type. Said tool-electrode comprises a conductive body having opposing lower and upper surfaces, two opposing main side surfaces, lower and upper regions that are stacked in a die-sinking direction of the tool-electrode, the lower region comprising the lower surface and part of the main side surfaces, the upper region comprising the upper surface and the other part of the main side surfaces. The body is provided, at least in the lower region, with a plurality of openings chosen from channels or slots; a channel is an opening that opens onto at least one of the upper and lower surfaces; a slot is an opening that opens onto the lower surface and onto the two main side surfaces; the diameter of each channel and the distance between two side walls of each slot is ≤ twice the die-sinking machining gap; each slot has a height, in the die-sinking direction, that is ≥ three times the depth of the recess to be made.

IPC Classes  ?

• B23H 1/04 - Electrodes specially adapted therefor or their manufacture
• B23H 1/06 - Electrode material
• B23H 9/00 - Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects

Abstract

This method for de-energizing an electric machine comprising a superconducting inductor and an armature comprises a step (12) of injecting an electric current into the armature so as to generate losses in the superconducting inductor until the temperature of the superconducting inductor increases above a predefined temperature threshold at which the inductor stops superconducting.

IPC Classes  ?

• H02P 3/24 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an ac motor by applying dc to the motor
• H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load

Abstract

The invention relates to a method which comprises the following steps: - measuring a pressure difference at terminals of a metering device (22) supplied with fuel by a pump (20); - calculating a position of a valve (24) regulating the pressure difference; - determining at least one estimated position of the valve from the pressure difference and at least one reference function giving the pressure difference as a function of the position; - calculating at least one value representing a drift of the pump (20) using the calculated position and the estimated position; and - comparing the value with a predetermined threshold.

IPC Classes  ?

• F02C 7/232 - Fuel valves; Draining valves or systems
• F02C 9/26 - Control of fuel supply
• F02C 7/236 - Fuel delivery systems comprising two or more pumps

Abstract

The present invention concerns a metal powder for an additive manufacturing method, the metal powder comprising a nickel-based alloy comprising between 0.02% and 0.04% of carbon, between 18% and 22% of chromium, between 11% and 13% of cobalt, between 5% and 5.5% of niobium, between 3% and 3.5% of tantalum, between 3% and 3.4% of molybdenum, between 0.9% and 1.1% of titanium, between 0.4% and 0.6% of aluminium, between 0.003% and 0.005% of boron, not more than 0.5% of iron, not more than 0.1% of copper, not more than 0.1% of silicon, not more than 0.05% of manganese, not more than 0.01% of phosphorus, not more than 0.01% of zirconium, not more than 0.004% of magnesium, not more than 0.003% of sulfur, not more than 0.025% of oxygen, not more than 0.018% of nitrogen and not more than 0.003% of hydrogen.

IPC Classes  ?

• B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 10/36 - Process control of energy beam parameters
• B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 70/00 - Materials specially adapted for additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The invention relates to a method for characterising distortions in a plenoptic camera comprising an array of microlenses and a photosensitive surface, the method comprising the following steps: obtaining (101) a geometric model of the array of microlenses indicating how the microlenses are positioned relative to one another; obtaining (102) an image of a test pattern acquired by the plenoptic camera having a characteristic point; identifying (104) a set of adjacent microlenses of the array which project the characteristic point into different pixels of the image, for each of the of adjacent microlenses; calculating (108) a difference between a pixel of the image into which the characteristic point is projected by the microlens and a pixel of the image arising from a point on the photosensitive surface passing through an optical axis of the microlens; estimating (110) radial distortion caused by the array of microlenses.

IPC Classes  ?

• G06T 7/80 - Analysis of captured images to determine intrinsic or extrinsic camera parameters, i.e. camera calibration
• G06T 5/00 - Image enhancement or restoration

Abstract

The present invention relates to a control method for controlling the voltage in an electrical bus (130) connecting an electrical power source (111, 112, 113) to an electrical receiver (121, 122), the control method comprising the steps of: receiving an operating setpoint; receiving a voltage measurement; comparing the voltage measurement with a template; and controlling the electrical power source.

IPC Classes  ?

• H02J 1/12 - Parallel operation of dc generators with converters, e.g. with mercury-arc rectifier

Abstract

A AAsFFBCC) of the solid (S), a step (E7) of moving the particles (P) followed by the determining (E3), calculating (E4, E5) and solving (E6) steps.

IPC Classes  ?

• G06F 30/28 - Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
• G01M 9/08 - Aerodynamic models
• G06F 111/10 - Numerical modelling
• G06F 113/08 - Fluids

Abstract

The present invention relates to a method for manufacturing a lightweight epoxy resin core, to a lightweight epoxy resin obtained by the method of the invention, and to the uses thereof for producing cores for hollow parts intended, in particular, for: - the aeronautical, aerospace and automotive industries; - medical and wind turbine technologies; - wagons; - ships; - and sporting goods.

IPC Classes  ?

• C08J 9/08 - Working-up of macromolecular substances to porous or cellular articles or materials; After-treatment thereof using blowing gases generated by a previously added blowing agent by a chemical blowing agent developing carbon dioxide
• C08G 59/00 - Polycondensates containing more than one epoxy group per molecule; Macromolecules obtained by reaction of epoxy polycondensates with monofunctional low-molecular-weight compounds; Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups

Abstract

The invention relates to a method (100) for manufacturing a blade, the method comprising preparing (102) a spar preform arranged in a first mold, the spar preform comprising a core and a root; a first injection step (104) of injecting a first thermosetting resin into the spar preform; partially polymerizing (106) the first resin in the spar preform until partial vitrification of the first thermosetting resin; positioning (108) a body preform around the core of the spar preform; injecting (110) a second resin into the blade body preform; and completely polymerizing (112) the first resin and the second resin.

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/72 - Encapsulating inserts having non-encapsulated projections, e.g. extremities or terminal portions of electrical components
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 11/26 - Fabricated blades
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

This control device for a propulsion system, which comprises means for computing a blade-pitch setpoint for at least one propeller of the propulsion system, the computing means using a predictive model of the performance of the propeller that takes into account at least one flight speed so as to adapt a blade-pitch angle setpoint, is characterized in that the predictive model of the performance of the propeller is configured to use polar curves implemented in the form of a mathematical law.

IPC Classes  ?

• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• B64C 11/30 - Blade pitch-changing mechanisms

Abstract

This process comprises: - carrying out non-planar three-dimensional forming of at least one segment of a flexible printed circuit board (900) comprising an electrically insulating polymer film (902), and, on at least one side of the polymer film (902), a metallization (904); then - carrying out electrodeposition in which a conductive layer is deposited on at least the metallization (904) of at least the formed segment.

IPC Classes  ?

• H05K 1/02 - Printed circuits - Details
• H05K 1/18 - Printed circuits structurally associated with non-printed electric components
• H05K 3/24 - Reinforcing of the conductive pattern

Abstract

A method for the tomographic analysis a part in order to detect anomalies (30), the method comprising the following steps: - acquiring at least one three-dimensional image (25) of the part by means of a tomography device; - subdividing the image (25) into elementary subparts (27); - analyzing a grayscale distribution in each subpart (27) and obtaining at least one parameter representative of this grayscale distribution for each subpart (27); - comparing the one or more parameters obtained for each subpart (27) with standard values characteristic of a defect-free region and detecting abnormal subparts (31) for which the one or more parameters differ from the standard values; - determining risk regions, which comprise each abnormal subpart (31) and each subpart (33) adjacent to at least one abnormal subpart; and - analyzing the risk regions to detect the anomalies (30) in the part.

IPC Classes  ?

• G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]
• G06T 7/10 - Segmentation; Edge detection

Abstract

The invention, according to one aspect, relates to a method for automatically diagnosing a part of a rotating machine on the basis of a time signal generated by the rotating machine, comprising the following steps: - Constructing a diagram from the signal, comprising the following sub-steps: - Splitting the signal into a plurality of sub-signals; - For each sub-signal, calculating the Fourier transform of the sub-signal to obtain a vibratory energy per frequency; - Constructing the diagram, the diagram being a matrix having a plurality of rows each corresponding to a speed of rotation of the rotating machine, and a plurality of columns each corresponding to a frequency of the Fourier transform divided by a speed of rotation of the rotating machine, the matrix comprising, for each row and each column, the corresponding vibratory energy; - Supervised training of an artificial neural network to make it capable of providing, from a diagram, an operating class comprised in a set of operating classes including at least one nominal operating class and one defective operating class, the artificial neural network being trained on a training database comprising training diagrams each associated with an operating class; and - Using the trained artificial neural network on the constructed diagram to provide an operating class for the rotating machine.

IPC Classes  ?

• G06N 3/08 - Learning methods
• G01M 13/028 - Acoustic or vibration analysis
• G01M 13/045 - Acoustic or vibration analysis

Abstract

The present invention relates to an assembly for lubricating and pressurizing a chamber for a turbomachine comprising at least one lubricated chamber (112) protected by two seals (112-1,112-2), the turbomachine further comprising a primary passage (103) surrounding the at least one lubricated chamber (112), through which flows a primary flow (F1) that passes through at least one compressor (102, 104) of the turbomachine, the assembly comprising an electric compressor (116) supplied with air and connected to the at least one lubricated chamber (112) in order to let pressurized air into the chamber (112) through the seals (112-1,112-2).

IPC Classes  ?

• F01D 11/04 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements

Abstract

The present invention relates to a casing (8) for a turbomachine (1), comprising: - a plurality of arms (11) extending from an internal hub (9) to an external hoop (10); - wire harnesses (13) that are configured to connect a first electrical apparatus (14) which is arranged radially outside the external hoop (10) and a second electrical apparatus (14) which is arranged radially inside the external hoop (9); and - a sheath (16) extending within an arm (11) at a distance from the wall (12) of the arm (11), the sheath (16) comprising an inner face (17) which defines an internal cavity that is configured to accommodate the wire harnesses (13); and - at least one shim (18) mounted in the sheath (16), each shim (18) being configured to keep the wire harnesses (13) at a distance from an internal face (17) of the sheath (16).

IPC Classes  ?

• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/12 - Cooling
• H02G 3/04 - Protective tubing or conduits, e.g. cable ladders or cable troughs

Abstract

The invention relates to an assembly comprising a disk (2) of a moving gear of a turbomachine comprising an axis of rotation and teeth (21, 21'). The teeth each comprise a first lateral surface (21a) on one side and a second lateral surface (21b) on the other side. Slots (23) are formed between the teeth and each comprise a bottom surface (23c) that connects the first lateral surface (21a) of one tooth to the second lateral surface (21b) of an adjacent tooth. A first radial surface (2c) and a second radial surface (2d) are formed on either side of the disk and delimit the slots and teeth. A shim (1, 1') is mounted in a slot and comprises an outer surface (1e) that partly covers the first and second radial surfaces, a base (10) in contact with the bottom surface, a first lateral arm (12a) and a second lateral arm (12b) which are connected to one another by the base. Each of the lateral arms is in contact with a portion of the first lateral surface of one tooth and with a portion of the second lateral surface of the adjacent tooth, respectively. A first axial retaining element (15c, 15ac, 15bc) for axially retaining the shim abuts the first radial surface in order to retain the shim in the slot in the axial direction of the disk of the moving gear.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The invention relates to an assembly for a turbomachine having a longitudinal axis (X), the assembly comprising a distributor (40) borne by an annular part (30) attached to an outer casing (20), the distributor (40) comprising an outer annular platform (42) from which a radial annular wall (44) extends radially outward, said wall bearing an annular attachment lug (45) extending longitudinally upstream from the radial annular wall (44), the assembly comprising a cooling circuit that comprises an inner annular chamber (61) radially delimited by the outer annular platform (42) and the annular part (30), and downstream by the radial annular wall (44), an intermediate annular chamber (62) radially formed outside the annular attachment lug (45) and in fluid communication with the outer casing (20), means for fluidly communicating the inner annular chamber (61) with the intermediate annular chamber (62) which are each formed in the annular attachment lug (45) of the distributor (40).

IPC Classes  ?

• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings

Abstract

The present invention relates to a system (25) for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system comprising: - at least a first rotary electric machine (26) connected mechanically to the low-pressure shaft (12) by means of a coupling device (27), - a second rotary electric machine (26') connected mechanically to the high-pressure shaft (11) by means of an accessory gearbox (17), and - said first electric power module (28) and said second electric power module being connected electrically to an internal electrical network (22) of the turbomachine, - a generator (15) coupled to the accessory gearbox (17) and intended to supply an electrical network of the aircraft (16) with electricity, and - a control device (30) suitable for controlling the assistance for start-up of the turbomachine by at least one rotary electric machine (26, 26'), for compensating for the power consumed by the generator (15), and for implementing the distribution between the power absorbed by the high-pressure shaft (11) and the power absorbed by the low-pressure shaft (12) according to operating phases of the turbomachine.

IPC Classes  ?

• F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• F02C 7/275 - Mechanical drives

Abstract

Disclosed is a device for generating electrical energy, comprising: a first loop for circulating a first two-phase element and comprising at least one first evaporating structure (2) fluidly connected to a first condensing structure (3); a second loop for circulating a second two-phase element and comprising a second evaporating structure (4) fluidly connected to at least one second condensing structure (5), the evaporating temperature of the second two-phase element being lower than the evaporating temperature of the first two-phase element; and a set of thermoelectric elements (8) having a first face (8a) connected to the first condensing structure (3) and a second face (8b) connected to the second evaporating structure (4).

IPC Classes  ?

• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• B64D 41/00 - Power installations for auxiliary purposes
• H10N 10/13 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the heat-exchanging means at the junction
• F28F 13/00 - Arrangements for modifying heat transfer, e.g. increasing, decreasing

Abstract

The present invention relates to a blade (1) for an unducted fan of a turbomachine, the blade (1) comprising an airfoil (10) formed of plurality of airfoil sections (S) that are stacked along an airfoil axis (P), the blade (1) being characterized in that a difference in sweeps corresponding to a difference between the leading edge sweep (F(BA)) and the trailing edge sweep (F(BF)) of one and the same airfoil section (S) is negative, and substantially between -30° and 0°, for any airfoil section (S) whose height is between 10% and 30% of the airfoil height (H), and is positive, and substantially between 0° and +40°, for any airfoil section (S) whose height is between 50% and 90% of the airfoil height (H).

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The present invention relates to a part (10) for an aircraft turbine engine, said part (10) comprising a body and a heat barrier coating (4) located on said body, said coating comprising: - a lower heat insulation layer (42) which is located on said body and which comprises at least one geopolymer, - an intermediate metal heat dissipation layer (46) which is located on the lower layer, and - an upper heat insulation layer (44) which is located on the intermediate metal layer and which comprises at least one geopolymer.

IPC Classes  ?

• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and

Abstract

BPHPBPHPBPHPBPHPBPHPBPHPBPHPBPHPHP) in question.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes

Abstract

The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, the magnetic ring comprising a predetermined number of pairs of poles, the magnetic ring being formed by at least one oriented-flux magnet, comprises: - determining a characteristic dimension (20) of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, - determining a reference value (20) equal to the minimum value out of a predetermined reference length and twice the value Pi, - comparing (21) the characteristic dimension of the magnet with the reference value, and - if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.

IPC Classes  ?

• H02K 1/2783 - Surface mounted magnets; Inset magnets with magnets arranged in Halbach arrays
• H02K 15/03 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets

Abstract

The present invention relates to a method for producing (1) a reel for a filament, said method comprising the steps of: - extruding (2) a blend of crystalline or semicrystalline binders and at least 90% by weight or 60% by volume of metal or ceramic powder so as to obtain a filament; - quenching (3) said filament at a predetermined quenching temperature in order to reduce, by between 5% and 15%, a degree of crystallinity in said binders; - winding (4) said filament around the reel at a temperature of between 10°C and a temperature below the quenching temperature.

IPC Classes  ?

• B29C 48/05 - Filamentary, e.g. strands
• B29C 48/88 - Thermal treatment of the stream of extruded material, e.g. cooling
• B29C 48/02 - Small extruding apparatus, e.g. handheld, toy or laboratory extruders

Abstract

The present invention relates to a blade (1) for a ducted fan of a turbomachine, the blade (1) comprising an airfoil (10) formed of a plurality of airfoil sections (S) stacked along an airfoil axis (P), the blade (1) being characterized in that a difference in sweep (Delta) corresponding to a difference between the leading edge sweep (S(LE)) and the trailing edge sweep (S(TE)) of one and the same airfoil section (S) is: - substantially identical for any airfoil section (S) having a height of between 10% and 20% of the airfoil height (H), and/or - substantially identical for any airfoil section (S) having a height of between 75% and 90% of the airfoil height (H).

IPC Classes  ?

• F01D 5/14 - Form or construction
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps