Abstract: A method for separating a part blank from a support, wherein the support and the part blank are manufactured by additive manufacturing. The support includes an inner cavity containing a fluid. The separation method includes a heating of the support to deform the support by fluid expansion in the inner cavity until the support is separated from the part blank.

Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Abstract: A system comprising a secure element cooperating with a telecommunication terminal is provided. The secure element or the terminal comprises files in which MCC/MNC codes of MNOs are stored. The telecommunication terminal is configured to select the files in order to attach the terminal to the telecommunication network of a MNO. The secure element or the terminal also comprise a file, called National like network file, for storing national network codes (MCC/MNC) of networks of the country of the Home PLMN of the secure element. The terminal selects the National like network file in order to try to connect the terminal to one of the networks referenced in the National like network file. Other embodiments are disclosed.

Abstract: Provided is a method to operate a subscriber identification module connected to a communication equipment configured to operate in a cellular network and communicatively coupled with a remote server. The method includes receiving from the communication equipment an information element indicating a time range relating to a suspend time of the communication equipment, receiving from the remote server a target access time information element indicating an expected time for an access request from the subscriber identification module to the remote server, and determining a suspension time period considering the suspend time range. The method includes providing to the communication equipment the suspension time period, and in case after resuming from the suspension instructed by the communication equipment the accumulated duration of at least one successive time period derived from the suspension time period exceeds the target access time, sending a polling message.

Abstract: A gate for controlling oncoming traffic on a roadway (e.g. a highway). The gate comprises an arm movable between an extended position in which the arm extends into a given portion of the roadway to inform the oncoming traffic that the given portion of the roadway is closed and a retracted position in which the arm does not extend into the given portion of the roadway and thus leaves open the given portion of the roadway for the oncoming traffic. The gate also comprises a control system comprising an actuator and configured to support the arm and move the arm between the extended position and the retracted position. The arm may be quite long and vertically wide to close more of the roadway and be clearly visible to the oncoming traffic, while the gate may be crash-tested (i.e., compliant with crash-testing criteria), the control system may be compact, and the gate may be reusable and easily repairable if crashed into.

Abstract: Provided is a method for attaching a terminal cooperating with a secure element to the network of a MNO of a visited country. The method includes steps of switching a set of files of said secure element to a new value, including a new SUPI, called entity support SUPI; Building at the level of said secure element an entity support SUCI; Routing an attachment request to said support entity with said entity support SUCI; Decrypting in said support entity said entity support SUCI back in said entity support SUPI; and Swapping said support entity SUPI to the SUPI corresponding to the MNO of the home country. If an authentication is performed that is positive, an attachment acknowledgement message is sent to connect said terminal to said network of said MNO of said visited country.

Abstract: A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.

Abstract: A gate for controlling oncoming traffic on a roadway (e.g. a highway). The gate comprises an arm movable between an extended position in which the arm extends into a given portion of the roadway to inform the oncoming traffic that the given portion of the roadway is closed and a retracted position in which the arm does not extend into the given portion of the roadway and thus leaves open the given portion of the roadway for the oncoming traffic. The gate also comprises a control system comprising an actuator and configured to support the arm and move the arm between the extended position and the retracted position. The arm may be quite long and vertically wide to close more of the roadway and be clearly visible to the oncoming traffic, while the gate may be crash-tested (i.e., compliant with crash-testing criteria), the control system may be compact, and the gate may be reusable and easily repairable if crashed into.

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 including a gas generator, a fan, and an electrical machine, the stator of the electrical machine being connected to a power electronic circuit by at least one electrically conductive bar which extends substantially radially relative to the axis inside an IGV which forms part of a bladed angular segment, the bar being configured to be disassembled and removed from the turbine engine by disassembling and removing the segment.

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: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

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: 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: An aircraft turbine engine includes a gas generator and a fan arranged upstream of the gas generator and configured to generate a main gas flow, of which one portion flows in a stream from the gas generator to form a primary flow, and of which another portion flows in a stream around the gas generator to form a secondary flow. The gas generator includes a low pressure body having a rotor driving the fan by means of a crown of a mechanical planetary reduction gear. The turbine engine further includes an electrical machine mounted coaxially around the reduction gear and having a rotor rotated by the crown of the reduction gear, and a stator extending around the rotor of the electrical machine.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: Methods, systems, and computer storage media for providing a data analytics index associated with a crisis-recovery data analytics engine in a data analytics system. The data analytics index is a consolidated single index representation of a set of variables associated with a set of consumer behaviors. The crisis-recovery data analytics engine supports generating the data analytics index associated with a pre-crisis period and a crisis-recovery period. In operation, a crisis-recovery dataset—associated with a set of variables of a set of consumer behaviors that support quantifying recovery from a crisis event—is accessed. The set of consumer behaviors are selected based on a crisis-recovery machine learning model that is trained on a pre-crisis dataset and a crisis dataset for selecting the set of consumer behaviors. A data analytics index is generated based on the crisis-recovery dataset. A data visualization comprising crisis-recovery data indicating recovery from the crisis event is generated.

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: 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 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.