Abstract: The invention relates to an electric module (11) of a fan of axis A, comprising a fan (12) provided with blades (13) which are rotatably movable inside a casing (40), and an electric machine comprising a rotor (60) secured to the fan (12) and a stator (66) integrated into said casing (40), characterized in that the rotor (60) of the electric machine is integrated into the fan (12) and in that it comprises a removable ring (62) which captures only axially and transversely from the radially outer ends (64) the blades (13) of the fan (12) and which is received inside said stator (66) which is integrated into the casing (40).

Abstract: An aircraft turbomachine, including a fan that is able to rotate inside a casing, and an electric machine including a rotor secured to the fan and a stator secured to the casing, wherein the rotor of the electric machine includes a ring that is able to rotate inside the stator, which is linked by arms to a cone mounted upstream from the fan.

Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.

Abstract: Methods and systems for predicting are disclosed. Records for transactions can be stored, each record comprising an indication identifying items involved in a transaction and an indication of a time elapsed between the transaction and a previous transaction. The records for transactions can be analyzed to produce a probability that the items will be involved in a next transaction.

Abstract: The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.

Abstract: Systems and methods for predicting are described herein. A record for each of a plurality of events associated with user transactions can be stored. A sequential plurality of the events can be analyzed using a unidirectional long short term memory (LSTM) and first and second dense neural network layers configured to receive output from the LSTM network.

Abstract: A method for manufacturing a part by additive manufacturing, the part to be manufactured including at least one portion to be held forming an angle of less than 45° with respect to a building direction of the part to be manufactured, the portion to be held having a first lateral surface and a second lateral surface opposite each other, the method comprising the steps of: providing a digital model of the part to be manufactured, adding to the digital model at least one holding element positioned on one side of the portion to be held, so as to be in contact with said first lateral surface or said second lateral surface.

Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.

Abstract: A sealing assembly for a turbine is provided. The turbine includes stages each including a nozzle blade extending between radially inner and outer platforms, the outer platform including a spoiler which delimits a groove. The assembly includes a ring, a tab, and an anti-wear foil. The ring is to be attached to an outer casing of the turbine. A part of the sealing tab is engaged in a first housing of a ring sector of the ring and another part in a second housing of an adjacent ring sector. The anti-wear foil, open upstream, is mounted in the groove. The downstream end of the ring sectors are to be engaged in the anti-wear foil. Each of the first and second housings is formed by a slot. The tab is bent and disposed in the slots so that a downstream end of the tab extends out of the slots.

Abstract: An aircraft turbine engine includes a low-pressure body and a high-pressure body, as well as means for drawing power on said low-pressure body, said means having a first shaft for drawing power, the radially inner end of said first shaft bearing a first bevel gear meshed with a first idler bevel wheel driven by the low-pressure body, the turbine engine further having a first annular bearing support which extends about an axis and is rigidly connected to a stator. The first bearing support includes a first cylindrical portion which extends coaxially with a second substantially cylindrical portion of the idler wheel, said first and second portions being guided one inside the other by bearings, and the idler wheel is driven by the low-pressure body by means of an annular damping piece which is independent of the first bearing support.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).

Abstract: In embodiments, methods and systems for order management and processing based on a distributed commerce platform are provided. A distributed commerce platform supports end-to-end integrated product publication, order-management and payment services. In particular, the distributed commerce platform supports components based on Application Programming Interfaces (API) that standardize the implementation of a distributed commerce solution or configuration of off-site buying experiences. Using the distributed commerce platform, merchants can concurrently offer, sell, and process orders for products through a plurality of different affiliate channels. The distributed commerce platform can also be implemented as a federated portal from which a merchant can identify affiliate channels to publish product objects, access the plurality of affiliate channels and define configurations for processing objects of the merchant's distributed commerce solution.

Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

Abstract: A fiber distribution system (10) includes a fiber distribution hub (20, 300); at least one fiber distribution terminal (30, 100); and a cable (40) wrapped around a spool (110) of the fiber distribution terminal (30, 100). The fiber distribution terminal (30, 100) includes a spool (110) and a management tray (120) that rotate together. A second connectorized end (40b) of the cable (40) is held at a fiber optic adapter (125) on the tray (120). After dispensing the first connectorized end (40a) to the hub (20), an optical splitter (70, 130, 140) can be mounted to the tray (120). The splitter (26, 70, 130, 140, 306) has output adapters at which patch cords (50) can be inserted to connect subscribers to the system. The fiber distribution hub can use the same format of splitters (26, 70, 130, 140, 306). Other distributed splitter systems are provided with splicing and/or adding of splitters as needed.

Abstract: The invention relates to a device (26) for cooling an annular outer turbine casing (17), the device (26) comprising at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, said tube (27) having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged axially opposite each other, an air inlet manifold (28), the inlet of the tube (27) opening into said manifold (28), characterized in that the tube (27) comprises at least one intermediate wall extending over a circumferential portion of the tube (27) from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.

Abstract: The invention relates to a sealing assembly for a turbine (1) rotor of a turbomachine, said turbine comprising an outer casing (4) and a plurality of rotor impellers (3) and nozzles (2), the sealing assembly comprising a sealing ring (7), attached to the casing (4), consisting of a plurality of ring sectors (70a, 70b) and surrounding the impeller (3), a sealing tab (8, 8?) being engaged, in a first slot (73a) of a ring sector (70a) and in a second slot (73b) of an adjacent ring sector (70b).

Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).

Abstract: A fiber distribution system (10) includes a fiber distribution hub (20, 300); at least one fiber distribution terminal (30, 100); and a cable (40) wrapped around a spool (110) of the fiber distribution terminal (30, 100). The fiber distribution terminal (30, 100) includes a spool (110) and a management tray (120) that rotate together. A second connectorized end (40b) of the cable (40) is held at a fiber optic adapter (125) on the tray (120). After dispensing the first connectorized end (40a) to the hub (20), an optical splitter (70, 130, 140) can be mounted to the tray (120). The splitter (26, 70, 130, 140, 306) has output adapters at which patch cords (50) can be inserted to connect subscribers to the system. The fiber distribution hub can use the same format of splitters (26, 70, 130, 140, 306). Other distributed splitter systems are provided with splicing and/or adding of splitters as needed.

Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.