Abstract

The invention relates to a casing (200) of a turbine engine compressor, comprising openings (201) which are made in the thickness of the casing from an inner face (2001) of the casing and arranged next to one another on a circumference of the casing, characterised in that it also comprises a movable ring (220) which is formed by at least two annular portions, is present on an outer face (2002) of the casing opposite the openings and is able to move along the circumference of the casing so as to open and close the openings of the casing in order to activate or deactivate a casing treatment, the movable ring comprising the same number of slits (202) as there are openings in the casing.

IPC Classes  ?

• F04D 29/52 - Casings; Connections for working fluid for axial pumps
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the like; Balancing by influencing boundary layers

Abstract

The invention relates to a system comprising: a harness for a weaving loom and a device for monitoring the manufacture of a preform woven by the loom, the monitoring device comprising: a plurality of sensors, each sensor of the plurality of sensors being connected to one of the plurality of strings and being configured to measure a deformation of the string, the deformation being induced by a force exerted by the loom on the string to which the sensor is connected; and a processing unit connected to the plurality of sensors and configured to analyse the deformation so as to identify a manufacturing abnormality on at least one string.

IPC Classes  ?

• D03C 3/40 - Constructions of lifting-cords
• D03C 3/42 - Arrangements of lifting-cords

Abstract

One aspect of the invention relates to a method (2) for monitoring a turbomachine (1) comprising a stator (11), a rotor (12) comprising blades (13), a strain gauge (15) attached to the stator (11) and a position sensor (14) for detecting the position of the blades (13), the gauge (15) being configured to capture a first signal comprising two components, the position sensor (14) being configured to capture a second signal representing the position of each blade (13), the method (2) comprising, on each revolution of the rotor (12), with one revolution being detected on the basis of the second signal: acquiring (21) the first and second signals; angularly resampling (22) the first signal; extracting (23) the first component from the resampled first signal by sliding-filtering the resampled first signal; and, on the basis of the filtered resampled first signal, calculating (24) at least one contact indicator for each blade (13) for the revolution.

IPC Classes  ?

• F01D 11/20 - Actively adjusting tip-clearance
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

Tooling (40) for manufacturing a blade (10) made of composite material for a turbomachine, in particular of an aircraft, comprising: - a mould (30) and a counter-mould (34) which define between them a cavity (32) configured to receive a woven preform, the cavity (32) having a first part (Z1) configured to receive a shield (22) and at least one edge of the preform, and a second part (Z2) configured to receive at least part of the remainder of the preform, and - elements (42, 44, 46) for managing the temperature of the cavity (32), which elements are configured to heat the first and second parts (Z1, Z2) of the cavity (32) at different temperatures during at least one step of a method for manufacturing the blade (10).

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]
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• 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 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29C 35/16 - Cooling

Abstract

The invention relates to a turbine engine comprising: - a first module comprising a speed reducer (3) having an input shaft (12), - a second module comprising a low-pressure compressor which is connected to the first module, - a third module comprising a low-pressure shaft which is centred on a longitudinal axis X and which comprises an upstream end connected to the input shaft, and - a locking device configured to axially immobilise the second module with respect to the first module and to the second module, the locking device comprising: - a first nut (60) screwed onto a thread of the low-pressure shaft and in contact with an annular projection of the second module, - an anti-displacement member (65) configured to axially lock the first nut, - a second nut (73) screwed onto a thread of the second module and configured to axially immobilise the anti-displacement member, and - a third nut (93) screwed onto the anti-displacement member.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• 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 7/32 - Arrangement, mounting, or driving, of auxiliaries

Abstract

The invention relates to a method for manufacturing a part made of composite material, said method comprising: - the arrangement of a fibrous preform (10) in a mould comprising an impregnation chamber (201), the impregnation chamber (201) being closed by a membrane (230) separating the impregnation chamber (201) from a compaction chamber (202), - the injection of an impregnation fluid (5) into the impregnation chamber (201), and the injection of a compression fluid (6) into the compaction chamber (202) so as to apply pressure to the membrane (230), - the aspiration of the compression fluid (6) present in the compaction chamber (202), the method being characterized in that the surface (230b) of the membrane (230) present on the side of the compaction chamber (202) comprises a plurality of grooves (235a, 235b).

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B28B 1/26 - Producing shaped articles from the material by slip-casting, i.e. by casting a suspension or dispersion of the material in a liquid-absorbent or porous mould, the liquid being allowed to soak into or pass through the walls of the mould; Moulds therefor
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/83 - Carbon fibres in a carbon matrix
• B28B 3/00 - Producing shaped articles from the material by using presses; Presses specially adapted therefor
• B28B 7/34 - Moulds, cores, or mandrels of special material, e.g. destructible materials
• B28B 7/46 - Moulds; Cores; Mandrels characterised by means for modifying the properties of the moulding material for humidifying or dehumidifying

Abstract

The invention relates to a turbomachine comprising: a first splitting edge capable of separating an incoming air flow into a radially internal air flow and a secondary air flow; a second splitting edge capable of separating the radially internal air flow into a primary flow and a tertiary flow which traverses a tertiary flow path that is radially external to a primary flow path traversed by the primary flow; a heat exchanger (18) arranged in the tertiary flow path; and an inner casing (28); characterized in that the exchanger comprises a body (32) and a flange (32.1) which extends radially inside and projects from the body, the flange being attached to the inner casing, the exchanger comprising, downstream of the flange, a downstream portion (40) to which a fire wall (46) forming a heat shield is attached.

IPC Classes  ?

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

Abstract

The invention relates to a turbine engine comprising: a first splitting edge capable of separating an incoming air stream into a radially internal air stream and a secondary air stream; a second splitting edge capable of separating the radially internal air stream into a primary stream and a tertiary stream which traverses a tertiary-stream flow path that is radially external to a primary-stream flow path traversed by the primary stream; a heat exchanger (18) arranged in the tertiary-stream flow path; and an inner casing (28); characterized in that the exchanger comprises an upstream portion (50) comprising a collar (52) which projects from a body (32) of the exchanger in the upstream direction, the collar being accommodated in a floating manner in a groove (54) that runs circumferentially in the inner casing.

IPC Classes  ?

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

Abstract

The invention relates to an inter-turbine casing (8) for a turbine engine of the turbine vane frame type, which casing acts as a turbine distributor in such a turbine engine, the inter-turbine casing comprising an inner shroud (9), an outer shroud (10), a plurality of arms (11) extending between the inner shroud and the outer shroud, and at least one set of N splitter vanes (12) positioned circumferentially between two successive arms. Each splitter vane has a mid-height axial chord shorter than the mid-height axial chord of the arms. The two successive arms define a reference position for each of the N splitter vanes. These reference positions are evenly spaced circumferentially between the two successive arms. At least one splitter vane (12-1) of the set of N splitter vanes is circumferentially offset from the reference position thereof. The invention further relates to a turbine engine assembly comprising the inter-turbine casing and a turbine (7) extending downstream of the inter-turbine casing (8) and comprising at least one movable vane (13) extending radially. The invention further relates to a turbine engine comprising the turbine engine assembly. The invention further discloses a method for positioning a splitter vane within an inter-turbine casing.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a sealing device (1) comprising: a ring (10) that comprises a main sealing lip (12) and a secondary sealing lip (14), the main sealing lip having an inner surface (11), the secondary sealing lip (14) having a radial surface (13), and a casing (20) comprising a cylindrical portion (22) and a radial portion (24), the radial portion (24) having a contact surface (23), the ring (10) being biased so as to apply the radial surface (13) of the secondary sealing lip (14) against the contact surface (23) of the casing (20), wherein the sealing device (1) has at least one leakage path (30) that extends between the secondary sealing lip (14) and the casing (20).

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F16J 15/30 - Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings with sealing rings made of carbon
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F16J 15/34 - Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member

Abstract

The invention relates to a method for detecting an anomaly in the operation of a component of an aircraft associated with at least one status indicator, the method comprising, for at least one acquired time sequence (Seq1, Seq2) comprising acquired values of said at least one indicator, steps of: - determining (E20) an approximated time sequence (Seq1*, Seq2*) of approximated values of said acquired values by means of an approximation module (AE1, AE2); - determining (E30) an overall abnormality score (A1, A2) for the acquired time sequence (Seq1, Seq2) on the basis of differences between the acquired values (Seq1, Seq2) and the approximated values; and - detecting (E40) an anomaly in the operation of the component on the basis of a comparison of the overall abnormality score with a first threshold, the approximation module being configured to minimize approximation errors between time sequences of reference values and time sequences of approximated values.

IPC Classes  ?

• G06F 17/18 - Complex mathematical operations for evaluating statistical data
• G06N 20/00 - Machine learning
• G05B 23/00 - Testing or monitoring of control systems or parts thereof

Abstract

The invention relates to a method for manufacturing a steel part (10) for an aircraft, the method comprising the welding of at least two steel elements (12, 14) to one another so as to form this part (10), the application of a resistance treatment to the part (10) which comprises austenitization (30) followed by quenching (32) and at least one step of tempering (34), and the local application, to a weld bead (16) between the at least two elements (12, 14), of a softening treatment comprising heating the weld bead (16) to a softening temperature lower than the temperature Ac1 at which the steel starts to transform from ferrite into austenite.

IPC Classes  ?

• C21D 1/25 - Hardening, combined with annealing between 300 °C and 600 °C, i.e. heat refining ("Vergüten")
• C21D 1/42 - Induction heating
• C21D 9/50 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for welded joints
• C22C 38/02 - Ferrous alloys, e.g. steel alloys containing silicon
• C22C 38/04 - Ferrous alloys, e.g. steel alloys containing manganese
• C22C 38/44 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
• C22C 38/46 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
• B23K 15/00 - Electron-beam welding or cutting
• B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
• B23K 26/21 - Bonding by welding
• C21D 1/40 - Direct resistance heating

Abstract

The invention relates to manual deburring tool (1) comprising: - a consumable carbide plate (10) having deburring edges (12), and - a casing (20) which is configured to be grasped manually and has an internal cavity (22) for housing the plate, the casing (20) comprising a body (25) and a cover (27) removably attached to the body so as to allow the insertion of the plate (10) into the cavity (22) and the removal of said plate from the cavity, the housing comprising at least one opening (26) that opens into the cavity and exposes a deburring edge (12).

IPC Classes  ?

• B24D 15/02 - Hand tools or other devices for non-rotary grinding, polishing, or stropping with rigidly-supported operative surface
• B26B 29/00 - Guards or sheaths for hand cutting tools; Arrangements for guiding hand cutting tools
• B26B 5/00 - Hand knives with one or more detachable blades

Abstract

The invention relates to a method for producing an abradable ceramic composite coating on a substrate, the method comprising: obtaining (E1) a composition (30) in powder form comprising a matrix powder and a ceramic filler hydrated precursor powder having a lamellar crystallographic structure, wherein the ceramic filler powder represents from 5 to 40% of the combined volume of the matrix powder and the ceramic filler powder; compressing the prepared powder composition at a pressure greater than 150 MPa; and a step of reactive sintering (E2) the obtained powder composition, during which the pressure is maintained at a temperature of less than 550°C, and the particles of the matrix powder in the sintered powder composition have an aspect ratio of 2 or greater. The invention also relates to an abradable ceramic coating obtained according to the method. The invention also relates to a superalloy part for a turbomachine, for example a turbine part, comprising such a coating.

IPC Classes  ?

• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
• C04B 35/488 - Composites
• C04B 35/486 - Fine ceramics
• C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
• C04B 35/645 - Pressure sintering
• C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
• C04B 41/52 - Multiple coating or impregnating
• C04B 41/87 - Ceramics
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products
• 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
• C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• C04B 111/00 - Function, property or use of the mortars, concrete or artificial stone

Abstract

The invention relates to a propeller blade or vane (10) for a turboprop engine, made from composite material and comprising a matrix-densified fibrous reinforcement, the propeller blade or vane comprising, in the direction of its span (DL), a root (12) and an aerodynamic profile (11). The fibrous reinforcement comprises a fibrous preform having three-dimensional weaving, with a root preform portion and an aerodynamic-profile preform portion. The fibrous preform comprises a disconnected portion delimiting a housing that forms a cavity (14) extending both into the root (12) and into the aerodynamic profile (11). A spar (130) is present in the cavity (14), the spar comprising an aerodynamic-profile shaping portion (131) positioned in a first portion (142) of the cavity (14) and a root shaping portion (132) positioned in a second portion (141) of the cavity. The root (12) has a rotationally symmetrical shape.

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• 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 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29C 70/72 - Encapsulating inserts having non-encapsulated projections, e.g. extremities or terminal portions of electrical components
• 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]
• B64C 11/26 - Fabricated blades
• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The invention relates to a cluster of wax models, around which a mould (1) for manufacturing a plurality of bladed elements by lost-wax casting is intended to be formed, the model having a longitudinal axis (X) and comprising: a replica of a casting cup (2), a replica of a central sprue (3), a plurality of replicas of mould elements (4), and a plurality of replicas of source feed ducts (5) of the mould elements (4). According to the invention, each replica of a source feed duct (5) is connected to a replica of a mould element (4) via replicas of fluid communication elements (6a, 6b, 6c).

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/04 - Use of lost patterns
• B22C 9/08 - Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
• B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles

Abstract

Sector (6) of a guide vanes assembly for a turbine of an aircraft turbomachine, the sector (6) comprising an outer platform (7) and an inner platform (8) which are coaxial along an axis (X), the sector (6) further comprising at least one blade (9) which connects the outer and inner platforms (7, 8) together, characterized in that the blade (9) is variable-pitch about an axis of rotation (Y) of the blade (9), the blade (9) comprising an aerodynamic body (11) delimited radially by a head and a root, the head being placed with a first functional clearance in an opening of the outer platform (7), the root being placed with a second functional clearance in a cavity of the inner platform (8), the axis of rotation (Y) of the blade (9) being located downstream of the head and the root.

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

Abstract

The invention relates to a device for guiding a shaft of an aircraft turbine engine, the device comprising: - a rolling bearing (10, 11); - an annular bearing support (22); and - an oil film compression damping system (19) comprising: - two annular sealing segments (26, 27); and - a first oil supply circuit (33), this first circuit being connected to an annular supply groove (34), characterized in that the damping system further comprises: - a second oil supply circuit (41), this second circuit being connected to at least one annular temperature control groove (40) which is independent of the supply groove (34) and which runs around one of the sealing segments (26, 27).

IPC Classes  ?

• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearings; Lubricating
• F01D 5/10 - Antivibration means

Abstract

The invention relates to a guide vane (33B) for attachment to a stator shroud of a gas turbine engine, comprising: - a profiled part (36B) intended to extend in a gas flow in order to guide the gas flow, the profiled part (36B) having a pressure-side surface (43B) and a suction-side surface (44B), and - a platform (34B) having a guide surface (45B) from which the profiled part (36B) extends, a first lateral surface (46B) and a second lateral surface (47B), the second lateral surface (47B) being able to be arranged facing a first lateral surface (46A) of an identical adjacent guide vane (33A), forming a raised portion which prevents a parasitic transverse flow of the gas flow, while creating a depression which at least partially compensates for the obstruction of the gas flow by the raised portion.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

The invention relates to a device for injecting a combustible mixture, for a combustion chamber (100) of an aircraft turbine engine turbine, which comprises, about a longitudinal axis (X), a tubular central channel (1), a first annular channel (2) about the central channel and a second annular channel (3) about the first annular channel (2), the channels (1, 2, 3) opening into the combustion chamber at a first lip (9) of the central channel (10), of a second lip (10) of the first annular channel and of an end (11) of the second annular channel, the first annular channel comprising, upstream of the second lip (10), a device (5, 6, 7) for injecting dihydrogen into the first annular channel (2) in an air flow (8) passing along the longitudinal axis of the first annular channel so as to create a dihydrogen-air mixture flowing towards the combustion chamber.

IPC Classes  ?

• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
• F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Abstract

The present invention relates to a method for depositing a continuous coating of aluminium oxide on a metal substrate by means of induction heating-assisted pressurised, temperature-controlled chemical deposition, the method comprising a solvothermal synthesis step based on an aluminium oxide precursor dissolved in a water-co-solvent mixture heated by induction to a temperature of between 400°C and 700°C and a pressure of between 1 MPa and 25 MPa. It also relates to a device (100) for depositing an aluminium oxide on a metal substrate (104) by means of pressurised, temperature-controlled chemical deposition, which device comprises: - an chamber (102) delimited by walls forming a closed volume (V), the chamber being intended to contain a heated and pressurised fluid, the material of the walls of the chamber being transparent to electromagnetic radiation; - a support (106) transparent to electromagnetic radiation intended to support the metal substrate (104) located inside the chamber; - an induction heating device (109) surrounding the outside of the chamber (102) so as to be able to heat the metal substrate (104) positioned on the support (106); - an inlet (116) located in the upper portion of the chamber (102) and configured to allow a precursor material previously dissolved in water to be added to the chamber (102); - an inlet (120) located in the lower portion of the chamber (102) and configured to allow a fluid to be added to the chamber (102); - at least one outlet (124) configured to purge the volume (V); - a sapphire window (112) arranged in the upper portion of the chamber, allowing the temperature of the metal substrate (104) to be controlled by a bichromatic pyrometer (114) arranged outside the chamber; - a set of polymer seals (200); - a metal assembly (202) rigidly screwed together by metal columns (204) containing a circulating fluid maintained, by a cryostat (206), at a temperature of 20°C.

IPC Classes  ?

• C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
• C01B 13/36 - Methods for preparing oxides or hydroxides in general by precipitation reactions in solutions
• C01F 7/448 - Dehydration of aluminium oxide or hydroxide, i.e. all conversions of one form into another involving a loss of water by wet processes using superatmospheric pressure, e.g. hydrothermal conversion of gibbsite into boehmite

Abstract

The invention relates to a method for producing a moulded part and to the three-dimensionally moulded part itself, comprising a composite material including a fibrous preform and a resin, the part having a cavity (230') filled with a cellular material (50). The cellular material comprises an expanded cellular polymeric material.

IPC Classes  ?

• B29C 44/14 - Incorporating or moulding on preformed parts, e.g. inserts or reinforcements the preformed part being a lining
• 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 70/70 - Completely encapsulating inserts
• B64C 11/26 - Fabricated blades
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• B29C 33/52 - 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 soluble or fusible
• B29C 53/82 - Cores or mandrels
• B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

The invention relates to a nickel-based superalloy comprising, in weight percentages, 5.0 to 6.0% aluminium, 6.5 to 8.5% tantalum, 0 to 1.0% titanium, 1.0 to 4.0% cobalt, 5.0 to 8.0% chromium, 0 to 0.5% molybdenum, 3.0 to 4.0% tungsten, 3.75 to 5.75% rhenium, 3.5 to 5.0% platinum, 0.05 to 0.25% hafnium and 0 to 0.15% silicon, the remainder being made up of nickel and inevitable impurities. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and to a turbine engine (10) comprising such a blade (20A, 20B).

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The invention relates to a shim (400) for a turbine engine turbine disc (40), comprising a metal sheet forming an envelope that at least partially surrounds a tooth (42) of the turbine disc, the tooth separating a first and a second cavity (41) of the disc, each cavity being adapted to receive a root (20) of a movable blade (10) of the turbine. The envelope is adapted to at least partially cover: - each of the side walls (44) of the tooth, and - a downstream rim (46) of the tooth (42). The invention also relates to an assembly for a turbine engine rotor, to a turbine engine rotor, and to a method for installing a turbine engine rotor assembly.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots

Abstract

The present application relates to a blade (3) of a static vane assembly (2) of a turbine engine (1) comprising: - a blade root (8) comprising a fibrous reinforcer (13) comprising a first skin (12) and a second skin (12) separated by a cavity (14) that opens onto a lower face (15) of the blade root (8); - a fastener (6) configured to receive the blade root (8) and attach it to a hub (4) of the vane assembly (2), the fastener (6) comprising a platform (16) and a rib (17) protruding from the platform (16), the rib (17) being configured to penetrate the cavity (14) so as to extend between internal faces (12a) of the first skin (12) and of the second skin (12); and - an attachment system (18) configured to mechanically attach the first skin (12) and the second skin (12) to the rib (17) of the fastener (6).

IPC Classes  ?

• B64C 11/06 - Blade mountings for variable-pitch blades
• F01D 5/30 - Fixing blades to rotors; Blade roots
• B64C 11/26 - Fabricated blades
• B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby

Abstract

1233) across its width (L) by means of weaving between a plurality of warp yarns (30) and a plurality of weft yarns (31), the loom comprising: a plurality of heald wires (22), which are connected to a mechanism (11) capable of moving the heald wires in a vertical direction (Dv) between a reference position (PH) and a first position for opening the warp yarns, each heald wire being further provided with an eye (23) through which a warp yarn (30) passes, a rapier (40) arranged downstream of the heald wires (113), capable of drawing a weft yarn (31) from a bobbin (50), a device (90) for holding the fabric arranged downstream of the plurality of heald wires (22) and of the rapier (40), comprising two bearing surfaces (93, 94) arranged on either side of the fabric (T) to compress the fabric between the bearing surfaces (93, 94), characterised in that at least a first bearing surface (93) is shaped so as to be at least partially complementary to a surface of the fabric.

IPC Classes  ?

• D03D 25/00 - Woven fabrics not otherwise provided for
• D03D 49/20 - Take-up motions; Cloth beams

Abstract

A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includes one or more engine loads and an external electrical connection for communicating electrical power between the turbine engine and an electrical system of an aircraft. The turbine engine includes a power management system including a high voltage DC busbar configured to communicate electrical power between the first and second electric machines and the engine loads and the external electrical connection. The power management system includes a control system configured to control power offtake from and injection to the first and second electric machines, and controls power delivered to the one or more engine loads and the external electrical connection.

IPC Classes  ?

• F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/275 - Mechanical drives

Abstract

The invention relates to a navigation assistance method for a mobile system, the method comprising: - generating training data, comprising: o obtaining a sequence of images of an environment acquired by a camera (2) installed on board a vehicle (1) moving through the environment; o determining a footprint (EN) of the vehicle on the ground during the acquisition of an image in the sequence; o marking, as an area traversable by the mobile system, an image region (RI) corresponding to the projection of the footprint in another image in the sequence; - training, by machine learning, a model for predicting the traversability of the mobile system on a terrain by means of the training data; - obtaining images of a scene that are acquired by a camera installed on board the mobile system; and - predicting the traversability of the scene by supplying images of the scene to the model trained by machine learning.

IPC Classes  ?

• G05D 1/02 - Control of position or course in two dimensions
• G06V 20/00 - Scenes; Scene-specific elements
• G06V 10/774 - Generating sets of training patterns; Bootstrap methods, e.g. bagging or boosting
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
• G06V 20/56 - Context or environment of the image exterior to a vehicle by using sensors mounted on the vehicle

Abstract

The present invention relates to a turbomachine assembly (1), comprising: - a high-pressure compressor (5) configured to be driven by a high-pressure shaft (12); - a low-pressure compressor (4) configured to be driven by a low-pressure shaft (11), the low-pressure shaft (11) being configured to be driven at a lower speed than the high-pressure shaft (12); - a first power converter (21) configured to be driven by the high-pressure shaft (12); - an air-circulation system comprising a first air bleed port (9) positioned in the high-pressure compressor (5) and a second air bleed port (3) positioned upstream of the first air bleed port (9); - means (50) for determining an operating condition of the turbomachine assembly (1); and - a controller (40) configured to send, to the first power converter (21), instructions to transfer power from the high-pressure shaft (12) to the low-pressure shaft (11) or power from the low-pressure shaft (11) to the high-pressure shaft (12), according to the operating condition.

IPC Classes  ?

• 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 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

Abstract

The invention relates to an assembly screw comprising at least a threaded part (12A) and a non-threaded part (12C), the non-threaded part being provided with a strain gauge (22) that is sensitive to the instantaneous elongation of the non-threaded part and with an RFID tag (24) connected to the strain gauge by a wired link, the assembly allowing the wireless transmission of an electrical resistance value of the strain gauge representative of the instantaneous elongation.

IPC Classes  ?

• F16B 31/02 - Screwed connections specially modified in view of tensile load; Break-bolts for indicating or limiting tensile load

Abstract

Disclosed is a stator element (200) comprising: - an electrical conductor (202) that is elongate and hollow in order to define a flow channel (308) allowing a coolant to flow from one end to the other of the conductor (202), the conductor (202) being designed to pass an electric current; and - a connection element (208; 902) located at one of the ends of the conductor (202), comprising a fluid connection terminal (210) designed to allow coolant to enter the channel (308) or indeed coolant to exit from the channel (308), and an electrical connection terminal (212) designed to electrically connect the conductor (202). The conductor (202) and the connection element (208; 902) are formed of a single unitary part.

IPC Classes  ?

• H02K 3/22 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors consisting of hollow conductors
• H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil

Abstract

The invention relates to an assembly for a turbine engine, in particular of an aircraft, the assembly comprising a ring (2) with a rotationally symmetrical axis (O). According to the invention, the assembly comprises a plurality of support sleeves (12) each having a rotationally symmetrical axis (O) and each intended to receive a stud (8) of a variable pitch blade (3), each support sleeve (12) comprising a bore (30) passing right through the support sleeve (12) along the rotationally symmetrical axis (O), each support sleeve (12) being mounted on the ring (2) so as to pivot about a pivot axis (C, C') transverse to the radial axis (Z) and to the rotationally symmetrical axis (O).

IPC Classes  ?

• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• 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 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 7/02 - Rotors with blades adjustable in operation; Control thereof having adjustment responsive to speed
• F04D 29/64 - Mounting; Assembling; Disassembling of axial pumps
• B64C 11/06 - Blade mountings for variable-pitch blades

Abstract

The invention relates to a propeller (10) for an aircraft turbine engine, this propeller (10) having: - a hub (12), - vanes (14), - bearings (46, 48) for guiding the roots (18) of the vanes (14) into orifices (12a) in the hub (12), and - systems for retaining the roots (18) of the vanes (14) in the orifices (12a) in the hub (12) along the pitch axis (A), this system for retaining the root (18) comprising: + a ring (66) configured to be fitted in a groove (32) in the root (18), and + a screw-nut system (68) mounted on the root (18) between the ring (66) and one of the bearings (48). Figure for the abstract: Figure 4

IPC Classes  ?

• B64C 11/06 - Blade mountings for variable-pitch blades
• B64C 11/30 - Blade pitch-changing mechanisms
• 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 present invention relates to a protection element (45.1, 45.2) for a compressor drum (20), which is intended to be arranged at least in part between a blade root (25) and the compressor drum (20), comprising: - a first lateral wall (51.1, 51.2) comprising an inner portion (54.1, 54.2) intended to cover an inner rounded portion of a pocket (24), a bearing surface portion (55.1, 55.2) intended to cover a blade root bearing surface of the pocket (24), and an outer portion (56.1, 56.2) intended to cover an outer rounded portion of the compressor drum (20), - a connecting wall (53.1, 53.2) intended to cover an outer face of the compressor drum (20), and - a second lateral wall (52.1, 52.2) comprising a projecting portion (57.1, 57.2) intended to engage with a mounting groove (46.1, 46.2) formed in a vertical face of the compressor drum (20).

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

Abstract

The invention relates to a turbine engine (1) for an aircraft, comprising an annular lubrication enclosure (17) in which a speed reducer (12) is arranged, a system for lubricating the speed reducer (12) comprising a main lubrication circuit (24) and an auxiliary lubrication circuit (25) connected to the lubrication enclosure (17), the auxiliary circuit (25) being connected to an auxiliary reservoir (31), an inner shroud (19) extending around the lubrication enclosure (17) and the auxiliary reservoir (31) being located outside the outer shroud (18), one of the arms, referred to as the arm at 6 o'clock (20), being tubular and located at the 6 o'clock position, the lubrication enclosure (17) comprising a deflector (22) connected to the radially inner end (20a) of the arm at 6 o'clock (20) and configured to deflect oil flowing by gravity from the lubrication enclosure (17) towards the upstream compartment (21a) of the arm at 6 o'clock (20).

IPC Classes  ?

• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F01D 9/06 - Fluid supply conduits to nozzles or the like

Abstract

The present disclosure relates to a method for regulating the voltage (V_AC) of an electrical bus (411_AC) of an electrical system of an electrically hybridized turbomachine, the bus (411_AC) being intended to transport an AC current, the method (E) comprising controlling a magnetic flux within a permanent-magnet synchronous machine (401) of the electrical system, the machine (101) being connected to the bus (411_AC), the control being carried out on the basis of a voltage (V_AC) measured on the bus (411_AC) and of a rotational speed (Vrot) of the rotor of the machine (401) in relation to the stator of the machine (401) by driving an inverter (421) of the electrical system, the inverter (421) being connected to the bus (411_AC).

IPC Classes  ?

• H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks
• H02J 1/10 - Parallel operation of dc sources
• H02J 7/14 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle

Abstract

The present invention relates to a method for controlling an electrical system, comprising: processing a main command signal (IP) for commanding drawing of a mechanical power by the electrical system from an electrically hybridized turbomachine so as to extract from said signal a first frequency component (CF1) corresponding to a natural frequency of a first rotary body of the turbomachine and to generate a filtered first main signal (IF1) without the first frequency component (CF1); generating a first subsidiary command signal (CTRL_1) for commanding drawing of a mechanical power by the electrical system from the first rotary body based on the filtered first main signal (IF1); and generating a second subsidiary command signal (CTRL_2, CTRL_3) for commanding drawing of a power by the electrical system from an auxiliary power source based on the first frequency component (CF1).

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
• F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

Abstract

The invention relates to a device (100) for controlling and protecting a power transistor (102), comprising: - a nominal switching circuit (103) for the transistor; - a short-circuit detection circuit (105) which keeps the transistor in the conducting state and detects an increase or decrease in the voltage VGS of the transistor relative to reference voltages representative of a short-circuit of the transistor; - a protection circuit (107) which discharges the gate of the transistor after the detection of a short-circuit; and - a circuit (106) for measuring and controlling the nominal switching circuit, the short-circuit detection circuit and the protection circuit.

IPC Classes  ?

• H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit
• H03K 17/18 - Modifications for indicating state of switch
• H03K 17/16 - Modifications for eliminating interference voltages or currents

Abstract

According to one aspect, the invention relates to a device for de-icing a turbine engine blade (1) of axis Y, comprising a blade (2) that is rotatably movable about a pivot (20) of radial axis X and comprising an electrical resistor (60), an electrical power supply (6) connected to the electrical resistor (60), and a control lever (3) for the blade (2) connected to a control ring (11), the device being characterised in that the control lever (3) comprises a pair of conductive strips (32) connected to the lever for conjoint rotation and located on the side opposite the control ring (11) with respect to the radial axis X, and in that each conductive strip (32) of the pair of conductive strips comprises a first end in contact with a circular conductive track (4) connected to the electrical power supply (6) and comprises a second end connected to the electrical resistor (60).

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 25/02 - De-icing means for engines having icing phenomena

Abstract

The present invention relates to a method for applying a coating to a substrate (100) made of a nickel-based superalloy and to a turbine blade made of a nickel-based superalloy with a coating applied according to this method. The coating application method comprises at least a first chemical vapour deposition step for depositing chromium and/or cobalt on a surface of the substrate (100) and a second chemical vapour deposition step, after at least partially diffusing, in an underlying layer (102) of the substrate (100), the chromium and/or the cobalt deposited in the first chemical vapour deposition step, for depositing aluminium on the underlying layer (102) of the substrate (100).

IPC Classes  ?

• C23C 16/06 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the deposition of metallic material
• C23C 16/04 - Coating on selected surface areas, e.g. using masks
• C23C 16/56 - After-treatment
• C23C 10/28 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
• C23C 28/02 - 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 only coatings of metallic material
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The present invention relates to a method for obtaining an anti-oxidative coating for a titanium alloy part, comprising: - depositing a liquid composition on the part, comprising at least (i) a first sol-gel alkoxysilane precursor, (ii) a second precursor which is an organic-Inorganic sol-gel precursor of an element E1 or a salt of element E1, said element E1 being chosen from among silicon, aluminum, zirconium, titanium, tin, zinc, phosphorus and rare earths, (iii) a third precursor which is an organic-inorganic sol-gel precursor of an element E2 or a salt of element E2, said element E2 being chosen from among silicon, aluminum, zirconium, titanium, tin, zinc, phosphorus and rare earths, E1 and E2 not both being silicon, and (iv) water, and - hydrolyzing the first, second and third precursors of the deposited liquid composition and condensing same so as to form the anti-oxidative coating which comprises an interconnected mixed oxide network of the elements silicon, E1 and E2.

IPC Classes  ?

• C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material

Abstract

The invention relates to a system (3) comprising one or more light sources (21) which are each capable of delivering light pulses, one or more light detectors (31), an optomechanical head (160) and an optical fibre-connecting device (350) connecting the one or more light sources to the optomechanical head and connecting the one or more detectors to the optomechanical head, in which system the optomechanical head comprises at least three separate collimators optically associated with three optical fibres (51, 52, 53) of the connecting device, the three fibres being connected to the one or more light sources or being connected to the one or more light detectors.

IPC Classes  ?

• G01F 23/292 - Light
• B64D 37/00 - Arrangements in connection with fuel supply for power plant

Abstract

The invention relates to a method for obtaining an anti-oxidative coating for a titanium alloy part, comprising: - depositing a liquid composition on the part, comprising at least (i) a first precursor which is a metal-organic sol-gel precursor of a metal element E1 or a salt of metal element E1, said metal element E1 being chosen from among aluminum and zirconium, (ii) a second precursor which is an organic-inorganic sol-gel precursor of an element E2 or a salt of element E2, said element E2 being chosen from among aluminum, zirconium, titanium, tin, zinc, phosphorus or rare earths and being different from metal element E1, and (iii) water, and - hydrolyzing the first and second precursors of the deposited liquid composition and condensing same so as to form the anti-oxidative coating which comprises an interconnected mixed oxide network of elements E1 and E2.

IPC Classes  ?

• C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material

Abstract

A gear changing system for the driving of an apparatus by an accessory gearbox comprising: a train comprising a ring gear (5), a planetary gear (6) integral with an output shaft (4) and a planet carrier (7) integral with an input shaft (3), a clutch device (10) for the input shaft (3) and output shaft (4), and a locking device (9), the system comprising a first configuration in which the clutch device (10) is in the engaged position and the locking device (9) is in the disconnected position, to drive the output shaft (4) at the speed of the input shaft (3), and a second configuration (C2) in which the clutch device (10) is in the disengaged position (D) and the locking device (9) is in the connected position (B), to drive the output shaft (4) at a speed (N4) higher than the speed (N3) of the input shaft.

IPC Classes  ?

• F16H 3/54 - Gearings having only two central gears, connected by orbital gears with single orbital gears or pairs of rigidly-connected orbital gears comprising orbital spur gears one of the central gears being internally toothed and the other externally toothed
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F16H 59/46 - Inputs being a function of speed dependent on a comparison between speeds
• F16H 63/30 - Constructional features of the final output mechanisms
• F16H 59/68 - Inputs being a function of gearing status

Abstract

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

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
• B64D 41/00 - Power installations for auxiliary purposes
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

Abstract

The invention relates to a system (1) for heating a fuel for supplying an aircraft turbine engine (M), the heating system (1) comprising a fuel circuit (2); at least one first heat exchanger (41) configured to be mounted in an inner duct (V) of the turbine engine (M), the first heat exchanger (41) being configured to heat a heat-transfer fluid (F) with phase change using heat energy coming from an exhaust flow (FE); at least one second heat exchanger (42) configured to be mounted outside the inner duct (V) of the turbine engine (M), the second heat exchanger (42) being configured to heat the fuel flow (Q) using heat energy coming from the heat-transfer fluid (F), and at least one heat pipe device (5) mounted between the first heat exchanger (41) and the second heat exchanger (42), the heat-transfer fluid (F) circulating in the heat pipe device (5).

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

Abstract

The invention relates to a heat exchanger (1) for a turbomachine (4), in particular of an aircraft, having a longitudinal axis (X), the heat exchanger comprising a plurality of fins intended to be swept by a first fluid (2) in a first direction (D1), the fins extending in a second direction between a first panel (23) and a second panel (24), being arranged in several rows (R1, R2, Rn) in a third direction, and being arranged in a staggered manner, each row (R1, R2, Rn) of fins being parallel and connected to one another. According to the invention, the heat exchanger is annular, centred on the third direction and has an inner cylindrical surface (25a) defining an inlet (E) and an outer cylindrical surface (25b) defining an outlet (S), and the fins have a length (L) which decreases radially in the heat exchanger, in the first direction (D1), between the inner cylindrical surface and the outer cylindrical surface.

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
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

The present invention relates to a method and device (APP) for classifying and localising an object (OBJ) in an image sequence (IMG_SEQ). The proposed method comprises the steps of: • obtaining (S210) an image sequence (IMG_SEQ) of one or more images (IMG_1, …, IMG_N) acquired by a camera (CAM); and • determining (S220), by means of a classifier-localiser module (X_NN) from the image sequence (IMG_SEQ): o a class (ATR_CLAS_OBJ) assigned to the object (OBJ), the assigned class (ATR_CLAS_OBJ) being chosen from among a list of classes; and o an estimated position (EST_POS_OBJ) of the object (OBJ); the classifier-localiser module (X_NN) being configured, on the basis of reference image sequences (TR_DATA), to minimise a multi-objective loss function (F_LOSS) representative both of a classification objective and a localisation objective for classifying and localising, respectively, the objects in the reference sequences (TR_DATA).

IPC Classes  ?

• G06V 10/44 - Local feature extraction by analysis of parts of the pattern, e.g. by detecting edges, contours, loops, corners, strokes or intersections; Connectivity analysis, e.g. of connected components
• G06V 10/62 - Extraction of image or video features relating to a temporal dimension, e.g. time-based feature extraction; Pattern tracking
• G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks

Abstract

The invention relates to a heat exchanger (1) for a turbomachine, having a longitudinal axis (X), for performing an exchange of heat between a first fluid (2) and a second fluid (3), the heat exchanger comprising two panels (25, 26) and a plurality of fins (29) extending between the panels, the fins being arranged in a plurality of rows along the longitudinal axis and being arranged in a staggered manner, each row of fins being parallel and connected to one another, the heat exchanger being annular and centered on the longitudinal axis X. The panels extend radially between an inner cylindrical surface (34a) and an outer cylindrical surface (34b) of the heat exchanger, the fins having a first and second exchange surface which are defined in planes substantially perpendicular to the radial axis and intended to be swept by the first fluid along the longitudinal axis, the fins of each row further having a height, measured between the panels, that increases radially between the inner and outer cylindrical surfaces.

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
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

One aspect of the invention relates to a device for measuring the pitch angle of blades of a turbine engine with a first axis X, comprising: - a movable wheel which is centred on the first axis X and is provided with a plurality of blades arranged radially about the first axis X, each blade having a root at which it is mounted so as to pivot about a second radial pivoting axis Y, - a fixed frame of axis X, comprising at least one set of fixed magnetic sensors perpendicular to the first axis X, - the movable wheel comprising a first magnetic target, the magnetic target being attached to the movable wheel, each blade having a profile oriented along a third axis Z, - a first magnetic needle attached to a first blade and forming a first angle alpha with the third axis of the first blade, the first magnetic target serving as a reference for the first blade, the measuring device comprising a second magnetic needle attached to a second blade and forming a second angle beta with the third axis of the second blade, the second angle beta being different from the first angle alpha.

IPC Classes  ?

• G01B 7/30 - Measuring arrangements characterised by the use of electric or magnetic techniques for testing the alignment of axes
• B64C 11/30 - Blade pitch-changing mechanisms

Abstract

An electrical system (4) for a turbine engine, comprising: a bus (40); a first converter (410); a second converter (420); and a controller (412, 422, 4000).

IPC Classes  ?

• H02J 1/10 - Parallel operation of dc sources
• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
• H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network

Abstract

An assembly for a turbine engine, comprising: a first rotating body (222, 262, 282); a second rotating body (20, 220, 260, 280); and an electrical system (4) comprising: a bus (40); a first generator (411); a second generator (421); a first converter (410); a second converter (420); and a controller (412, 422, 432, 4000).

IPC Classes  ?

• H02J 1/10 - Parallel operation of dc sources
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

Abstract

The invention relates to a hydraulic control circuit (17) of a steering actuator (21) having a first and a second chamber (18, 19), for orienting the blades of an aircraft engine propeller, this circuit (17) comprising a high-pressure line (23) and a low-pressure line (24), a first protection valve (33) being able to assume a deactivated position or an activated position for placing the first chamber (18) in communication with the high-pressure line (23), a second protection valve (34) being able to assume a deactivated position or an activated position for placing the second chamber (19) in communication with the low-pressure line (24), each protection valve (33, 34) comprising a hydraulic activation inlet (37, 41) and a hydraulic deactivation inlet (38, 42) which can be pressurised in order to activate or deactivate these valves (33, 34). The circuit includes a solenoid protection valve (31) controlling an amplification valve (32) connected to the inlets of the protection valves (33, 34) in order to activate them upon the activation of the solenoid protection valve (31).

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F01D 7/02 - Rotors with blades adjustable in operation; Control thereof having adjustment responsive to speed
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• B64D 27/16 - Aircraft characterised by the type or position of power plant of jet type

Abstract

The present invention relates to an oil tank (40) for an aircraft turbine engine, comprising: an enclosure (54) capable of containing the oil and having a main axis intended to be oriented vertically in the mounting position; an oil inlet (66) in an upper portion of the enclosure; and an oil outlet (74) in a lower portion of the enclosure; characterised in that the oil tank further comprises: an impeller (80) arranged in the lower portion of the enclosure and capable of being rotated by drive means (82) so as to centrifuge the oil against a retaining wall (56.1) of the enclosure and against the oil outlet, and thus to maintain a supply of oil to said oil outlet during flight phases of the aircraft in zero or negative gravity.

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearings; Lubricating
• F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
• F04D 29/063 - Lubrication specially adapted for elastic fluid pumps

Abstract

The invention relates in particular to the assembly of annular sectors (100) of an annular multi-element acoustic component (10), each sector (100) comprising a plurality of rows of hollow complex acoustic elements (110) each having a shape that steadily narrows between a base and a vertex, each sector (100) comprising a plurality of first rows comprising the same number of hollow complex elements (110) and one or more second rows comprising one hollow complex element (110) less than the first rows, each second row further comprising a male attachment element (121) on one of the assembly edges (102a) and a female attachment element (122) on the other assembly edge (101a), the female attachment element (121) having the same size as a hollow complex element (110) in the assembly direction (Dc).

IPC Classes  ?

• G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects

Abstract

This aircraft propulsion system (12) comprises a turbine engine (20), a control system (24), a member (72) for determining a current engine speed (Rc) of the spool of the turbine engine (20), and a rotary machine (22) coupled to the transmission shaft of the turbine engine (20) to generate electrical power by the take-off of mechanical power from the transmission shaft. The control system (24) is configured to limit a current electrical power (Pc) generated by the rotary machine (22), at least when the engine spool is in an accelerating spool-up phase, to a maximum authorized power (Pmax) that is dependent on the current engine speed (Rc) prior to acceleration. The propulsion system further comprises a device (74) for determining the current electrical power (Pc) generated by the rotary machine (22), the control system (24) being configured to establish an engine speed which is above an idling speed (Rr) dependent on the current electrical power.

IPC Classes  ?

• F02C 7/26 - Starting; Ignition

Abstract

The present invention relates to optronic equipment (40) containing ballistic armor (10) comprising a three-dimensional reticular structure (20), which can in particular be regular and/or auxetic, and to a manufacturing process comprising a step of additively manufacturing at least the three-dimensional reticular structure (20).

IPC Classes  ?

• F41H 5/04 - Plate construction composed of more than one layer
• F41H 5/16 - Shields for ordnance
• F41G 1/00 - Sighting devices
• F41G 1/38 - Telescopic sights specially adapted for smallarms or ordnance; Supports or mountings therefor
• F41H 5/18 - Rotating shields
• F41H 5/26 - Peepholes; Windows; Covers therefor

Abstract

Disclosed is a turbomachine (10) having an oil-recovery device comprising, between mutually rotatable first and second members (14, 16), a tubular tab (54) of the first member (14) surrounded by a tubular extension (56) of a shroud (42) of the second member which defines, with a shroud (44) of the first member (14), an interface zone, the tubular extension (56) comprising an outer groove (60) opposite the tab (54), characterised in that the extension (56) axially surrounds the tubular tab (54) beyond an axial half-length (l) of the tab (54), has an inner diameter (d72, d74, d76) equal to an inner diameter (d42) of the outer shroud (42) of the second member (16) and has an outer diameter (D72, D74, D76) smaller than or equal to an outer diameter (D42) of the outer shroud (42), and in that the annular groove thereof has a rectangular cross-section.

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements

Abstract

The invention relates to an oil tank (40) for a turbomachine, the oil tank comprising an oil chamber having a main axis and walls defining a first compartment (56) and a second compartment (58) which is separated from the first compartment by a separating wall (60); a channel (62) extending into the first compartment from the separating wall; a feed (66) for oil mixed with air arranged in the second compartment; an oil outlet (74) comprising a duct (64) extending and opening into the first compartment; characterised in that the channel extends into the duct so as to ensure oil is supplied to the duct and is continued to be supplied to the duct during zero- or negative-gravity flight phases.

IPC Classes  ?

• F02C 7/06 - Arrangement of bearings; Lubricating
• F01D 25/18 - Lubricating arrangements
• F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
• F04D 29/063 - Lubrication specially adapted for elastic fluid pumps

Abstract

The invention relates to a bladed turbomachine assembly extending around an axis (AX), this turbomachine comprising a disk carrying blades (21a-21d), wherein each blade (21a-21d) extends radially from a root through which it is rigidly attached to the disc up to a heel comprising a platform (26a-26d), the assembly being characterised in that: – it comprises alternating blades (21a, 21c) that are prestressed in the upstream direction and blades (21b, 21d) that are prestressed in the downstream direction, the heel (24c) of each blade (21a, 21c) that is prestressed in the upstream direction tending to be offset in the downstream direction, the heel (24b) of each blade (21b, 21d) that is prestressed in the downstream direction tending to be offset in the downstream direction; – the adjacent pairs of blades having platforms (26a-26d) of which contiguous circumferential ends (27b-27d, 28a-28c) comprise protrusions (29a-29c) and notches (31b-31d) that slot into one another; – each protrusion (29a-29c) being pushed into a notch (31b-31d) in the axial direction (AX) by the prestresses of the blades carrying them.

IPC Classes  ?

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

Abstract

The invention proposes a turbomachine bladed assembly (10) comprising at least two adjacent blades (12), each blade (12) comprising a radial vane (14) and a platform (16) located at a free radial end of the vane (14), wherein the platform (16) of each blade (12) of the bladed assembly (10) is located circumferentially facing a platform (16) of the other circumferentially adjacent blade (12) of the bladed assembly (10), wherein the bladed assembly (10) comprises an insert (20) arranged circumferentially between the platforms (16) and which cooperates with the platforms (16), each platform (16) comprising a circumferential bearing face (32) with which one circumferential end of the insert (20) is in contact, the direction of the contact between each circumferential bearing face (32) and the insert (20) being oriented circumferentially with respect to the main axis A, the assembly comprising means for axially retaining the insert (20) between the two platforms (16) which comprise at least one finger (36) which is carried by the insert (20), projects circumferentially from the insert (20), and is received in an associated notch (38) formed circumferentially as a recess in at least one of the platforms (16), said at least one finger (36) and the associated notch (38) being designed to allow a relative movement of the insert (20) with respect to the platforms (16) in the radial direction.

IPC Classes  ?

• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding

Abstract

The invention relates to a Jacquard-type weaving loom (100) intended to produce a fibrous structure (200) by three-dimensional weaving between a plurality of warp threads (203) and a plurality of weft threads (204) extending in a horizontal direction (DH), the weaving loom comprising a reed (150) movable between a rest position upstream of the rapier and a position for striking a fell of the fibrous structure in a striking direction (DF) parallel to the horizontal direction. The reed (150) comprises at least two stationary portions (151, 152) at an angle to each other. The reed (150) is mounted on the weaving loom by means of a positioning mechanism (170) capable of orienting the reed about an axis of rotation (1710) so as to adjust an angular position of the stationary portions of the reed relative to a horizontal reference plane (PH). The weaving loom comprises vertical translation means (172, 160) capable of moving the reed or the fell (205) of the fibrous structure in the vertical direction (DV).

IPC Classes  ?

• D03D 1/00 - Woven fabrics designed to make specified articles
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
• D03D 25/00 - Woven fabrics not otherwise provided for
• D03D 49/60 - Construction or operation of slay
• D03D 49/62 - Reeds mounted on slay

Abstract

The present invention relates to a fibrous preform (1) of a core part of a fibrous reinforcement for a part made of composite material, the preform having a slender shape along a longitudinal direction (X) and being formed by three-dimensional weaving of first threads, extending in the longitudinal direction, with second threads that are transverse to said first threads, the preform comprising two longitudinal ends (3a; 3b) intended for articulation with other parts, as well as a median area (ZM) located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a first volume ratio of first threads relative to second threads which is greater than unity, and each longitudinal end having a second volume ratio of first threads relative to second threads which is less than the first ratio and closer to unity than the first ratio.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/22 - 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
• D03D 15/37 - 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 fibres or filaments with specific cross-section or surface shape
• D03D 25/00 - Woven fabrics not otherwise provided for
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• D03D 15/275 - Carbon fibres
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• F16C 7/02 - Constructions of connecting-rods with constant length
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B64C 25/02 - Undercarriages
• B60G 7/00 - Pivoted suspension arms; Accessories thereof
• F16C 11/04 - Pivotal connections
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The invention relates to a method for manufacturing a fibre preform for a part, comprising: - weaving a first core texture of elongate shape extending in a longitudinal direction and comprising, in cross section, a central portion (10) having, on its opposite sides, two edges each comprising two unravelled fibrous portions (16a; 16b), - shaping the first texture which involves at least opening out the unravelled portions to form a positioning surface (30) defined by the portions thus opened out and by an interleaved portion, situated between these opened-out portions, which may be formed by a prolongation (18a) of the central portion, - positioning a second, belt, texture over the opened-out lateral portions and the interleaved fibrous portion, the second texture forming a loop around the shaped first texture so as to define empty spaces for articulation to other parts.

IPC Classes  ?

• 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 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• D03D 15/275 - Carbon fibres
• D03D 25/00 - Woven fabrics not otherwise provided for
• F16C 11/04 - Pivotal connections
• F16C 7/02 - Constructions of connecting-rods with constant length
• B29B 11/04 - Making preforms by assembling preformed material
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B64C 25/02 - Undercarriages
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The invention relates to a method (100) for producing a plurality of blades (10) of height (Ha), which comprises: providing a mould (30) comprising an internal cavity bounded by an internal side face (34) of the mould which is axisymmetric about a longitudinal axis (X), the side face (34) extending along the longitudinal axis (X) at a height (Hf) which is greater than or equal to the height (Ha), the side face (34) defining a plurality of sections (34i) perpendicular to the longitudinal axis (X) of radius (Rfs), for each section (34i), the ratio of the height (Hf) of the side face (34) to the radius (Rfs) of the section (34i) being less than or equal to 2.0; rotating the mould about the longitudinal axis at a rotational speed of between 200 rpm-1and 800 rpm-1; and pouring a material into the internal cavity to centrifugally form a tubular part (20) along the longitudinal axis (X).

IPC Classes  ?

• B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
• B22D 13/02 - Centrifugal casting; Casting by using centrifugal force of elongated solid or hollow bodies, e.g. pipes, in moulds rotating around their longitudinal axis
• B22D 13/04 - Centrifugal casting; Casting by using centrifugal force of shallow solid or hollow bodies, e.g. wheels or rings, in moulds rotating around their axis of symmetry
• B22D 13/10 - Accessories for centrifugal casting apparatus, e.g. moulds, linings therefor; Means for feeding molten metal, cleansing moulds or removing castings
• B22D 13/12 - Controlling, supervising, specially adapted to centrifugal casting, e.g. for safety reasons
• B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
• B22D 31/00 - Cutting-off surplus material after casting, e.g. gates
• F01D 5/12 - Blades

Abstract

The invention relates to a pitch change mechanism (70) comprising a frame (72), an actuating cylinder (74) having a moving part (102) capable of translating relative to the frame (72), and a linkage system (78) connecting the moving part (102) to a variable-pitch vane (56) so as to convert the translation of the moving part (102) into a rotation of the variable-pitch vane (56). It further comprises a fluid transfer bearing (257) for supplying the actuating cylinder (74) with actuating fluid from a source (76) relative to which the actuating cylinder (74) is capable of rotating. The actuating cylinder (74) extends at least partly around the fluid transfer bearing (257).

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F16H 25/22 - Screw mechanisms with balls, rollers, or similar members between the co-operating parts; Elements essential to the use of such members
• F16H 25/24 - Elements essential to such mechanisms, e.g. screws, nuts
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• B64C 11/06 - Blade mountings for variable-pitch blades
• B64C 11/40 - Blade pitch-changing mechanisms fluid, e.g. hydraulic automatic
• F01D 5/30 - Fixing blades to rotors; Blade roots
• F04D 29/36 - Blade mountings adjustable
• F16H 25/20 - Screw mechanisms

Abstract

The present invention relates to an oil tank (40) for an aircraft turbomachine, the oil tank comprising: a main chamber (54) suitable for containing oil; an inlet (66) for oil mixed with air; and an oil outlet (72), the invention being characterised in that the oil tank further comprises: an auxiliary chamber (56) arranged inside the main chamber, the auxiliary chamber comprising a surrounding wall (60) and two end walls (61, 63) adjacent to the surrounding wall, at least one of the two end walls comprising at least one oil passage (62) in communication with the inside of the main chamber; at least one auxiliary inlet (67) opening tangentially to the surrounding wall and running across the main chamber; and an auxiliary outlet (74) tangential to a segment having the largest diameter (60.1) of the surrounding wall, the auxiliary outlet running across the main chamber in communication with the auxiliary circuit.

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearings; Lubricating
• F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
• F04D 29/063 - Lubrication specially adapted for elastic fluid pumps

Abstract

The invention proposes a bladed assembly (10) comprising two adjacent blades (12), and each blade (12) a platform (16) located at a free radial end, wherein the platform (16) of the first blade (12) comprises a lateral face (18) which is located circumferentially facing an associated lateral face (18) of the platform (16) of the second blade (12), the platform (16) of the first blade (12) coming into contact with the platform (16) of the second blade (12) via only a protrusion (20) which projects circumferentially with respect to the lateral face (18) of the platform (16) of the first blade (12) in the direction of the platform (16) of the second blade (12), and the protrusion (20) is received in a groove (22) formed in the platform (16) of the second blade, the protrusion (20) and the groove (22) each extending in a plane substantially perpendicular to a radial direction with respect to the main axis (A), the protrusion (20) comprising a radially outer face (24) which is oriented radially outwards and which bears radially against a bottom face (30) of the groove (22) which is oriented radially inwards, and the protrusion (20) and the groove (22) are located axially substantially in the middle of the platform (16) associated therewith.

IPC Classes  ?

• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding

Abstract

In a method for three-dimensional weaving of a fibrous structure (200) between layers of warp yarns (203) and layers of weft yarns (204), the weft yarns (204) are woven in a plurality of columns spaced apart from one another in a longitudinal direction (DL). The method comprises weaving deployment portions (222) in the fibrous structure that is interwoven with an adjacent portion, the weft yarns of the weft yarn columns of the adjacent portion (230) being juxtaposed in a first stacking direction perpendicular to the longitudinal direction (DL). During the process of weaving the deployment portions (222), the weft yarns of each weft yarn column (CT222) are positioned against the fell (205) of the fibrous structure in stacking directions (DS222) that are different from the first stacking direction.

IPC Classes  ?

• D03D 1/00 - Woven fabrics designed to make specified articles
• D03D 25/00 - Woven fabrics not otherwise provided for
• D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
• D03D 49/60 - Construction or operation of slay
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements

Abstract

The present invention relates to a fibrous preform of a core part of a fibrous reinforcement for a part made of composite material, the preform having a slender shape along a longitudinal direction (X) and being formed by first threads (C1-C16) extending in the longitudinal direction, with second threads (t1-t8) transverse to the first threads, the preform comprising two longitudinal ends intended for articulation with other parts, as well as a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a stiffening portion (102c) comprising non-woven first threads (C5-C12), and each longitudinal end comprising a three-dimensional weaving of the first threads of this stiffening portion with second threads.

IPC Classes  ?

• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29C 70/24 - 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
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B60G 7/00 - Pivoted suspension arms; Accessories thereof
• B64C 25/02 - Undercarriages
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• D03D 15/275 - Carbon fibres
• D03D 15/37 - 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 fibres or filaments with specific cross-section or surface shape
• D03D 25/00 - Woven fabrics not otherwise provided for
• F16C 7/02 - Constructions of connecting-rods with constant length
• F16C 11/04 - Pivotal connections
• B29B 11/14 - Making preforms characterised by structure or composition
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

A bladed assembly (40) for a turbomachine comprises a plurality of blades (42) distributed around an axis (28) and each comprising a vane (44) and a platform (46) formed at a free end of the blade (42). The platform (46) of each blade comprises a friction member (70) and an opening (72) that is oblong in a circumferential direction (C) with respect to the axis (28). The friction member (70) is engaged through the opening (72) formed in the platform (46) of a circumferentially adjacent blade (42) within the bladed assembly (40) with a clearance allowing the friction member (70) to move at least in the circumferential direction (C) within the opening (72). Mutual separation of the platforms (46) in the circumferential direction in operation due to vibrations of the blades causes the friction member 70 to rub against an edge of the opening 72 and thereby dissipate energy.

IPC Classes  ?

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

Abstract

The invention relates to a pitch-change mechanism (70) which comprises a frame (72), a moving part (102) which can be translated along a longitudinal axis (X), and a locking device (160). The locking device (160) comprises a support member (162) which is translatable along the longitudinal axis (X) between an operating position and a locked position, and a screw-nut system (164). The screw-nut system (164) is formed by a system of satellite roller screws (195) comprising a screw (176) which is translatably secured to the support member (162) and rotatably mounted about the longitudinal axis (X), and a nut (178) which is secured to the moving part (102). The screw (176) has an abutment surface (186) which is separated from the frame (72) when the support member (162) is in the operating position and bears against the frame (72) when the support member (162) is in the locked position.

IPC Classes  ?

• B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
• F16H 25/22 - Screw mechanisms with balls, rollers, or similar members between the co-operating parts; Elements essential to the use of such members
• F16H 25/24 - Elements essential to such mechanisms, e.g. screws, nuts
• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof

Abstract

The invention relates to a composite dielectric material comprising a thermosetting resin of benzocyclobutene (BCB) type and an inorganic filler, the inorganic filler comprising zirconium tungstate particles. The invention also relates to a power electronic module (1) comprising a substrate (10), a power electronic component (11) positioned on the substrate (10) and at least one encapsulating layer (12) formed from the composite dielectric material and positioned on the substrate (10) and the power electronic component (11).

IPC Classes  ?

• H01L 23/29 - Encapsulation, e.g. encapsulating layers, coatings characterised by the material
• C09C 1/00 - Treatment of specific inorganic materials other than fibrous fillers ; Preparation of carbon black
• H01L 23/31 - Encapsulation, e.g. encapsulating layers, coatings characterised by the arrangement

Abstract

The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement (62) and a matrix (64). The fiber reinforcement (62) includes a plurality of plies (66, 68) that are each formed of warp yarns (71) and weft yarns (72). The warp yarns (71) and weft yarns (72) include incomplete yarns (75, 76) that each have a terminal end (78) on the pressure side (40) or the suction side (42). The pressure side (40) and the suction side (42) each have at least one ply drop line connecting the terminal ends (78) of the incomplete yarns (75, 76) of the same ply (66, 68). The number of ply drop lines on the pressure side (40) is greater than the number of ply drop lines on the suction side (42) in a low region of the blade and/or in an extended region of the blade.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

One aspect of the invention relates to a device (30) for axially retaining a moving blade (10) of a low-pressure turbine in a recess (21) of a rotor disc of axis (X) of the turbine. This device comprises a stop part (40) intended to extend between an upstream face (11a) of a blade root (11) of the moving blade (10) and a downstream face (11b) of the root of the moving blade, the stop part (40) comprising: - a first wall (41) which forms an end stop for the upstream face (11a) of the blade root (11), - a second wall (42) which forms an end stop for the downstream face (11b) of the blade root (11), and - a connection surface (43) intended to extend between the first and the second wall (41, 42) along a radially inner end face (11c) of the blade root (11). Further features of the invention relate to a turbomachine rotor assembly and to a method for assembling moving blades (10) in the recesses (21) of an LP turbine rotor disc.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement and a matrix. The fiber reinforcement includes a plurality of plies that are each formed of warp yarns and weft yarns. The warp yarns and weft yarns include incomplete yarns that each have a terminal end on the pressure side or the suction side (42). The pressure side and the suction side (42) each have at least one ply drop line (82, 83) connecting the terminal ends of the incomplete yarns of the same ply. At least one ply drop line (82) includes at least one transverse portion (90) extending generally along a transverse direction (T), including an apex portion (92). The at least one apex portion (92) extends over at most 10% of the distance between the leading edge (44) and the trailing edge (46).

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement and a matrix. The fiber reinforcement includes a plurality of plies that are each formed of warp yarns and weft yarns. The warp yarns and weft yarns include incomplete yarns that each have a terminal end on the pressure side (40) or the suction side. The pressure side (40) and the suction side each have at least one ply drop line (80, 81) connecting the terminal ends of the incomplete yarns of the same ply. At least one ply drop line (81) has an end portion (96) that extends from the blade tip up to 90% of the blade height. Said end portion (96) extends generally along a direction of extent (E) forming an angle between 5° and 85° with the local tangent of the warp yarns.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

The invention relates to a method for transferring an adhesive onto a part intended to be glued to a carrier, the adhesive being in the form of a double-sided film comprising a separator on each side, the part comprising at least one internal concave portion that does not enable uniform application of the adhesive film once the separators have been removed. The invention is characterised in that, in order to enable uniform application of the adhesive film (40) to the part (12) and particularly to the internal concave portion, the method comprises the following steps: attaching the adhesive film to a punch (30) that matches the shape of the part within a range that approximately corresponds to the thickness of the adhesive film; removing the separator from the side of the adhesive film that is to be attached to the part; setting the part on the punch covered with the adhesive film that has had its separator removed; and transferring the adhesive film onto the part by creating a vacuum between the part and the punch by means of a vacuum device (48).

IPC Classes  ?

• C09J 5/00 - Adhesive processes in general; Adhesive processes not provided for elsewhere, e.g. relating to primers
• B29C 65/50 - Joining of preformed parts; Apparatus therefor using adhesives using adhesive tape

Abstract

The present invention relates to a flow-straightening stator (5) of an unducted thrust-generating assembly (3) comprising a plurality of blades (7) each having: - a tip (11) and a radially inner boundary (10) corresponding to an intersection between the blade (7) and a casing (8) of the turbine engine (1); - a skeleton (16); and - a deviation (δ) of the profile, corresponding to an absolute value of a difference between a tangent to the skeleton (16) at the leading edge (14) and a tangent to the skeleton (16) at the trailing edge (15) of the blade (7), of between 20° and 45° at the radially inner boundary (10) of the blade (7) and between 10° and 40° at the tip (11) of the blade (7).

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers

Abstract

The invention relates to an acoustic panel (9) for an aircraft turbomachine (1), the acoustic panel (9) comprising: - a first skin (10) formed from a first composite material having a first polymer matrix and reinforcing fibres embedded in the matrix, - a second skin (11) formed from a second composite material having a second, thermoplastic polymer matrix and reinforcing fibres embedded in the second matrix, and - a core (12) having a honeycomb structure, the core (12) being arranged between the first skin (10) and the second skin (11), characterised in that the second skin (11) comprises holes (11a) having a diameter that is smaller than 1 mm.

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression

Abstract

The invention relates to a titanium alloy comprising, as contents by weight: - 4.0% to 5.0 % of aluminium; - 3.50% to 4.50% of tin; - 1.0% to 4.0% of zirconium, - 2.0% to 5.25% of molybdenum; - 1.0% to 2.50% of niobium; - 0.10% to 0.25% of silicon; - 0.10% to 0.18% of oxygen; the balance being constituted of titanium and unavoidable impurities, the alloy further verifying that the criterion Aleq known as "equivalent aluminium content by weight" is less than or equal to 8.5%, the criterion Aleq being defined as Aleq =[Al]+[Sn]/3+[Zr]/6+10*[O] where [Al], [Sn], [Zr] and [O] are the weight contents respectively of aluminium, tin, zirconium and oxygen.

IPC Classes  ?

• C22C 14/00 - Alloys based on titanium
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

A stator vane assembly defining a chordwise direction and a crosswise direction perpendicular to the chordwise direction is provided. The stator vane assembly includes: an attachment plate; and an attachment assembly coupled to the attachment plate, the attachment assembly including: a first flange member attached to the attachment plate and extending along the chordwise direction; a second flange member attached to the attachment plate and extending along the chordwise direction, the first flange member spaced from the second flange member in the crosswise direction; and a crosswise support member extending between the first and second flange members and positioned between the attachment plate and the first flange member and between the attachment plate and the second flange member.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a blade comprising: - a blade body (12) having an aerodynamic profile comprising a first fibrous reinforcement obtained by three-dimensional weaving and comprising a first matrix in which the first fibrous reinforcement is embedded, the blade body part (12) comprising a cavity formed by a disconnection of the first fibrous reinforcement, - a blade root intended to be connected to a mechanism for the variable adjustment of the blade, and - a spar (13) comprising a core (14) made of composite material and two metal casings (21a, 21b) attached to the core (14) on either side of the core (14). The core (14) comprises a first part that extends inside the cavity of the blade body and a second part that forms the blade root. The two metal casings (21a, 21b) which are attached to the core (14) made of composite material extend over the second part and continue to extend over the first part inside the cavity of the blade body (12).

IPC Classes  ?

• B64C 11/26 - Fabricated blades
• B64C 27/473 - Constructional features
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• F01D 5/30 - Fixing blades to rotors; Blade roots
• B64C 11/06 - Blade mountings for variable-pitch blades

Abstract

The present invention relates to a conductor for an electric machine, and a method of making the conductor. The conductor comprises: two zones of higher electrical conductivity; and a zone of lower electrical conductivity. The zone of lower electrical conductivity comprises an electrically conductive material having a plurality of discontinuities in the electrically conductive material to provide the zone of lower electrical conductivity with a lower electrical conductivity than the zones of higher electrical conductivity. The zone of lower electrical conductivity separates the two zones of higher electrical conductivity along a lengthwise direction of the conductor.

IPC Classes  ?

• H02K 3/04 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
• H02K 15/04 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings, prior to mounting into machines
• H02K 3/02 - Windings characterised by the conductor material
• H02K 3/12 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors arranged in slots

Abstract

The invention relates to a jumper wire (6-A, 6-B, 6-C) for connecting an electrical cable (100-A, 100-B, 100-C) to a test device (2) with a view to diagnosing the state of health of the electrical cable (100-A, 100-B, 100-C), said jumper wire (6-A, 6-B, 6-C) comprising: an output port (7) configured to interact with an input port (3) of the test device (2), an input connector (8-A, 8-B, 8-C) configured to interact with a connector (110-A, 110-B, 110-C) of the electrical cable (100-A, 100-B, 100-C), and a data-storing element (9-A, 9-B, 9-C) that contains predetermined test data on the electrical cable (100-A, 100-B, 100-C) and that is electrically connected to the output port (7) by at least one data-transmitting wire (12), said data-storing element (9- A, 9-B, 9-C) being configured to deliver the test data to the test device (2).

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 31/50 - Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
• G01R 31/58 - Testing of lines, cables or conductors

Abstract

The invention relates to a heat exchanger device (1) for an aircraft turbomachine, which device comprises a heat exchanger body (30), an upstream hot-fluid header (12) attached to the heat exchanger body (30) and configured to collect a first fluid at a first temperature and to feed the first fluid to the heat exchanger body (30), an upstream cold-fluid header (22) attached to the heat exchanger body (30) and configured to collect a second fluid at a second temperature lower than the first temperature and to feed the second fluid to the heat exchanger body (30), the upstream hot-fluid header (12) at least comprising a double wall (120) forming a peripheral cavity (16) surrounding a main cavity (125) configured to receive a main flow of the first fluid, the peripheral cavity (16) being configured to receive a secondary flow of the first fluid or of the second fluid.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
• F28F 9/02 - Header boxes; End plates
• 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
• F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases

Abstract

One aspect of the invention relates to a method for manufacturing a self-stiffened intermediate casing for a turbomachine comprising the steps of: - draping at least one first preform, - draping at least one second preform, - positioning the first and the second preform side by side in order to form an assembly comprising a uniform inner surface and a raised outer surface, - draping the inner surface of the assembly so as to consolidate the assembly, and - co-curing the consolidated assembly. A further aspect of the invention relates to a self-stiffened intermediate casing for a turbomachine obtained using this method.

IPC Classes  ?

• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
• B29B 17/00 - Recovery of plastics or other constituents of waste material containing plastics
• B29B 17/04 - Disintegrating plastics
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

The invention relates to a navigation assistance device intended to be installed on board a moving system. This device comprises: a monocular camera capable of simultaneously acquiring a first image of a scene (In) with a first depth of field and at least one second image of a scene (If) with a second depth of field smaller than the first depth of field, a depth-estimating unit (23) configured to determine a depth map (Dm) of the scene from the first image of the scene and the at least one second image of the scene; a computer vision unit (24) configured to calculate a navigation path from the first image of the scene and from the depth map of the scene.

IPC Classes  ?

• G06V 20/56 - Context or environment of the image exterior to a vehicle by using sensors mounted on the vehicle
• G06V 10/147 - Optical characteristics of the device performing the acquisition or on the illumination arrangements - Details of sensors, e.g. sensor lenses
• G06V 10/10 - Image acquisition
• G06T 7/55 - Depth or shape recovery from multiple images
• B60W 60/00 - Drive control systems specially adapted for autonomous road vehicles

Abstract

The invention relates to a method (100) for automatically monitoring a plurality of rotating parts of rotating machines on the basis of a target database comprising a plurality of time signals from a distribution generated from each rotating part and on the basis of a source database comprising a plurality of time signals from a distribution S different from the distribution T generated from a source rotating part of a source rotating machine and being associated with an operating class, the monitoring being carried out by means of an adaptive deep learning model making it possible to adapt the source distribution to the target distribution, the deep learning module being trained by minimisation of a cost function relating to Gaussian kernel functions having a parameter σ; σ being calculated in each period on the basis of the difference in distributions weighted by a constant static value estimated on the basis of a Pascal's triangle.

IPC Classes  ?

• G01M 13/045 - Acoustic or vibration analysis
• G01M 13/028 - Acoustic or vibration analysis
• G06N 3/096 - Transfer learning
• G06N 3/08 - Learning methods
• G01N 29/44 - Processing the detected response signal

Abstract

The invention relates to a bearing (21) for a turbine engine comprising an oil film compression damper, including an inner sleeve (22) intended to receive an outer ring of a rolling bearing, an outer sleeve (23) surrounding the inner sleeve (22) and delimiting, with this inner sleeve (22), an axisymmetric cavity (27) supplied hydraulically in order to form a film of damping oil, this cavity (27) being closed at its ends by two segments (24, 26). According to the invention, the cavity (27) comprises a first portion (31) and a second portion (32) separated from one another by a movable segment (29) able to occupy a closed position in which it forms a controlled sealing barrier between the two portions (31, 32), and an open position in which the two portions (31, 32) communicate with one another, and it is the first portion (31) that is supplied hydraulically to form the film of oil.

IPC Classes  ?

• F16C 27/04 - Ball or roller bearings, e.g. with resilient rolling bodies
• F16C 35/077 - Fixing them on the shaft or housing with interposition of an element between housing and outer race ring
• F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings

Abstract

The invention relates to a method for controlling a turbomachine comprising a fan positioned upstream of a gas generator, the turbomachine comprising an electric motor forming a torque injection device for a high-pressure rotary shaft, in which method a fuel flow setpoint for a combustion chamber and a torque setpoint (Tcons) for the electric motor (ME) are determined, the control method comprising the steps of determining (El) a hybridisation rate (TH) corresponding to the ratio of the power (Pe) consumed by the electric motor (ME) to the power generated by the high-pressure rotary shaft (P2), determining (E2) a torque threshold (Tseuil) from the hybridisation rate (TH), limiting (E3) the torque setpoint (Tcons) to the torque threshold (Tseuil) if the torque setpoint (Tcons) is higher than the torque threshold (Tseuil).

IPC Classes  ?

• 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 9/48 - Control of fuel supply conjointly with another control of the plant

Abstract

The invention relates to an assembly comprising a propeller blade (10) and a system (34) for angularly setting the pitch of the blade (10) for an aircraft turbomachine, the blade (10) having a root (14) extending from an upper end connected to an airfoil (12) of the blade (10) to a free lower end (28), the root (14) having a bulging segment, which bulging segment is referred to as the "bulb" (32), the system (34) for angularly setting the pitch of the blade (10) comprising a cup (58) which is radially defined by an annular wall (58a) and which comprises a lower bottom closed by a bottom wall (58b) and an upper opening (58c) through which the bulb (32) is intended to be axially inserted into the cup (58), the bottom wall (58b) comprising a protrusion (200) which engages with a cavity (202) having a complementary shape in the free end (28) of the root (14).

IPC Classes  ?

• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

Abstract

The invention relates to a method for detecting a defect (DEF) in at least one gear of an aircraft turbomachine based on a vibratory signal (s(n)) of the gear, each gear having a determined meshing frequency (fc) corresponding to a carrier frequency, the method comprising steps consisting in estimating (E3) a target signal (x(n)) comprising a set of characteristic spectral lines based on a whitened vibratory spectrum (y(n)) obtained from a vibratory signal, the method comprising steps of determining, in the whitened vibratory spectrum (y(n)), a plurality of modulation blocks having a modulation index, each modulation block having a carrier coefficient that is dependent on a predetermined carrier frequency (fc) and on the modulation index and a plurality of modulation coefficients that are symmetric about the carrier coefficient.

IPC Classes  ?

• G01H 1/00 - Measuring vibrations in solids by using direct conduction to the detector
• G01M 13/021 - Gearings
• G01M 13/028 - Acoustic or vibration analysis

Abstract

The invention relates to a non-destructive inspection method based on 3D modelling of a part (200), comprising: - using an x-ray device (100) to acquire images of the part at various projection angles (I(n)); - computing projections based on the images acquired at the various projection angles; - in each of multiple iterations: - generating simulated projections corresponding to the computed projections, based on a reference model of an external surface of the part and on a vector µ of transformation parameters of the reference model; - modifying the vector µ with a view to reducing a discrepancy between the simulated projections and the computed projections; - determining a corrected model of the external surface through transformation of the reference model by way of the vector µ resulting from the iterations; - determining an effective model of the part by way of the corrected model.

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]
• G01B 15/04 - Measuring arrangements characterised by the use of electromagnetic waves or particle radiation, e.g. by the use of microwaves, X-rays, gamma rays or electrons for measuring contours or curvatures
• G06T 7/60 - Analysis of geometric attributes

Abstract

The invention relates to a method for detecting an anomaly in a system (110) of an aircraft (100), comprising: - obtaining a current series of measurements of one or more physical quantities (PT1, PT2) of the system (110), during a time period when the system (110) is in operation; - on the basis of the current series of measurements, providing, by means of an encoder-decoder (126), a current reconstructed series; and - comparing the reconstructed current series with the current series of measurements in order to obtain a current series of anomalies. The method further comprises: - computing a current distribution function of the current series of anomalies; - computing an area separating the current distribution function from a reference distribution function; and - comparing the area with a predefined threshold.

IPC Classes  ?

• G06N 3/04 - Architecture, e.g. interconnection topology
• G05B 23/02 - Electric testing or monitoring
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G06N 3/045 - Combinations of networks
• G06F 11/07 - Responding to the occurrence of a fault, e.g. fault tolerance
• B64D 15/04 - Hot gas application
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

The present disclosure relates to a heat exchanger for an electric machine. The electric machine includes a stator having a stator core and stator slots extending along a longitudinal axis of the stator, and a rotor assembly having a rotor configured to rotate about the longitudinal axis. The electric machine includes a coolant system having a stator cooling path providing a first coolant fluid in direct contact with the stator to flow around the stator core and through the stator slots. The coolant system also includes a coolant circuit providing a second coolant fluid to at least one rotatable component of the electric machine, such as at least one bearing. The coolant circuit and the stator cooling path are fluidically isolated from one another and arranged such that heat is exchanged between the first coolant fluid and the second coolant fluid at the stator.

IPC Classes  ?

• H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
• H02K 5/173 - Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings
• H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
• H02K 9/197 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil in which the rotor or stator space is fluid-tight, e.g. to provide for different cooling media for rotor and stator
• H02K 5/128 - Casings or enclosures characterised by the shape, form or construction thereof specially adapted for operating in liquid or gas using air-gap sleeves or air-gap discs

Abstract

The invention relates to a process for producing an optical device equipped with a nano-structured or micro-structured component (21) joined to one end of an optical fibre (30), the process comprising steps of: - providing a carrier (10) based on a photosensitive material (12) that is convertible into a vitreous material, and producing on one end (10A) of said carrier, by two-photon photopolymerization, a micro-structured or nano-structured component (21) based on a photosensitive material (22) that is convertible into a vitreous material; - carrying out one or more heat treatments so as to convert the material (12) of said carrier and the material (22) of said micro- or nano-structured component into vitreous material; subsequently, - joining and securing a region of a second end (10B) of said carrier (10), which end is opposite said first end (10A), to a zone of an end of the optical fibre (30), through localized fusion of said region and of said zone, of said carrier and of said optical fibre (30), respectively.

IPC Classes  ?

• G02B 6/26 - Optical coupling means
• G02B 1/00 - Optical elements characterised by the material of which they are made; Optical coatings for optical elements

Abstract

The invention relates to a turbomachine comprising a heat exchanger (11), a first circuit (13) for a first fluid, the first circuit (13) comprising two pipes (31, 33) in the heat exchanger (11), a second circuit (15) for a second fluid and a third circuit (17) for a third fluid, each of the second circuit and the third circuit comprising a channel (51, 71) in the heat exchanger (11), each channel (51, 71) being contiguous with one of the pipes (31, 33) so as to be in thermal contact with one of the pipes (31, 33), the channels (51, 71) being contiguous with one another so as to be in thermal contact with one another, the heat exchanger (11) comprising a section in which the pipes (31, 33) and the channels (51, 71) are locally parallel to one another.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F01D 25/12 - Cooling
• F01D 25/18 - Lubricating arrangements
• F02C 7/22 - Fuel supply systems
• F01D 25/20 - Lubricating arrangements using lubrication pumps

Abstract

The invention relates to an injection method for an injection device in a combustion chamber of an aircraft turbine engine, the injection device comprising an internal channel (6) surrounded by an external annular channel (8), the channels opening into the combustion chamber (4, 4') of the gas turbine, the method being characterised in that it comprises injecting a dihydrogen-air mixture (12a) with a hydrogen content greater than the stoichiometric amount into the internal channel (6) and injecting air into the external annular channel (8) so as to produce, at the outlet of the internal channel (6), a first flame front (30) resulting from rich combustion surrounded by a second flame front (31) resulting from lean combustion.

IPC Classes  ?

• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

The invention relates to a system (1) for controlling the temperature of a heat transfer fluid (F) configured to transfer heat to a fluid to be heated (Q) originating from a cryogenic tank (R), the control system (1) comprising: a loop (2) for circulating the heat transfer fluid (F), comprising an engine branch (21) and a tank branch (22); a first engine heat exchanger (41), configured to heat the heat transfer fluid (F) to a second temperature (T2) above a maximum operating temperature (Tmax); a mechanical pump (3) configured to circulate the heat transfer fluid (F) in the circulation loop (2), such that, in a second engine heat exchanger (42), a first part of the heat is transferred from the heat transfer fluid (F) to the fluid to be heated (Q) and the heat transfer fluid (F) is cooled to a third temperature (T3) below the maximum operating temperature (Tmax), before it leaves the engine enclosure (EN-M).

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 7/16 - Cooling of plants characterised by cooling medium
• F02C 7/224 - Heating fuel before feeding to the burner