Abstract: An electric module of a fan includes a fan provided with blades which are rotatably movable inside a casing, and an electric machine having a rotor secured to the fan and a stator integrated into said casing. The rotor of the electric machine is integrated into the fan and includes a removable ring which captures axially and transversely from the radially outer ends the blades of the fan and which is received inside said stator which is integrated into the casing.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clamping

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises:- an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and - an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

Abstract: A device (26) for cooling an annular outer turbine casing (17) includes at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (28), the inlet of the tube opening into the manifold, the tube (27) including at least one intermediate wall extending over a circumferential portion of the tube 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: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan located at an upstream end of the gas generator and configured to turn about said axis, and an electric machine of generally annular shape. The electric machine is coaxially mounted downstream of the fan and has a rotor coupled to rotate with the fan. The electric machine further includes a stator connected to an electronic power circuit by at least one rigid electrically-conductive bar.

Abstract: An electric module for an aircraft turbomachine includes an electric machine stator having an annular shape around an axis (A) and being configured to surround a rotor of the electric machine, and an annular support element of the stator. The support element includes an outer annular surface configured to be swept over by a gas stream (F) from the turbomachine with a view to conductively cooling the stator.

Abstract: A method for holding a part blank inside a holding assembly. The holding assembly includes a first holding portion. The first holding portion includes an inner cavity containing a fluid. The part blank and the first holding portion are at least partially manufactured by additive manufacturing. The holding method includes a heating of the holding assembly and the part blank to deform the first holding portion by fluid expansion in the inner cavity and to reduce a gap between the part blank and the holding assembly by expansion of the first holding portion in relation to the part blank.

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: 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: Methods and systems of using reinforcement learning for promotions. A first promotion is offered to a customer for a product and/or service. A first reward or penalty is determined, via a reinforcement machine learning model, based on the customer's reaction to the first promotion, wherein the reinforcement machine learning model is at a first state. Feedback to the reinforcement machine learning model is provided based on the first reward or penalty. A state of the reinforcement machine learning model is changed, based on the feedback, from the first state to a second state.

Abstract: The invention relates to a lubrication device (1) for a turbo machine, comprising: a rotor (2) rotating around an axis, at least one lubrication chamber (6) formed in the rotor (2), a stator (22) in which the rotor (2) is rotatably mounted, a bearing (11) for rotationally guiding the rotor (2), mounted between the rotor (2) and the stator, lubricating fluid supply means which supply at least the chamber (6) and the bearing (11), the lubricating fluid supply means comprising a nozzle (23) mounted on the stator provided with an ejection nozzle (34) at a free end of the nozzle (23), said nozzle (34) being configured to project the lubricating fluid into the chamber (6), characterized in that the nozzle (23) has a movable part (27) including said ejection nozzle (34), said movable part (27) being movable between a retracted position in which the ejection nozzle (34) is remote from the chamber (6) or at least partially located outside the chamber (6), and an extended position in which the nozzle (34) is closer

Abstract: A dynamic seal for a turbomachine, including a fixed portion provided with at least one abradable wear part and a movable portion including at least one lip arranged to interact with the at least one wear part during the rotation of the movable portion. The wear part includes a structure forming cavities arranged in one or more series such that, in each series, the cavities of this series are superposed radially with respect to the central axis, the structure being configured to limit or prevent the circulation of gas between each pair of radially adjacent cavities. A method for the additive manufacture of the fixed portion of this dynamic seal is also described.

Abstract: Methods and systems for using reinforcement learning to optimizing promotions. A promotion for a product and/or service is offered to a customer using a reinforcement learning model. The customer's reaction is observed. A reward or a penalty is collected based on the customer's reaction. The reinforcement learning model is adapted based on the reward or penalty.

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 blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

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 has a low-pressure body with a rotor driving the fan and a low-pressure compressor situated upstream from an intermediate housing. The turbine engine also includes an electric machine, mounted coaxially downstream from the fan and upstream from the intermediate housing. An intermediate shaft is driven by the rotor of the low-pressure body and drives rotors of the electric machine and of the low-pressure compressor.

Abstract: A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

Abstract: Aircraft turbine engine (10), comprising a gas generator (12) and a blower (14) arranged upstream of the gas generator and configured to generate a main gas flow (F), of which one portion flows in a stream from the gas generator to form a primary flow (36), and of which another portion flows in a stream around the gas generator to form a secondary flow (38), the gas generator comprising a low pressure body (12a) which comprises a rotor driving the fan by means of a crown of a mechanical planetary reduction gear (33), the turbine engine further comprising an electrical machine (62), characterised in that the electrical machine is mounted coaxially around the reduction gear and comprises a rotor (62a) rotated by the crown (33a) of the reduction gear, and a stator (62b) extending around the rotor of the electrical machine.