Abstract: The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members (18) of a turbomachine (10), the members (18) being configured to travel over an operating area comprising a first position P1 and a second position P2, the method comprising the steps of: —(E23) determining a first pivoting speed V1 from the first position P1 to the second position P2; —(E25) determining a second pivoting speed from the second position P2 to the first position P1; and—(E26) determining an anomaly in the operation of the system for positioning the members (18) if the first speed V1 is lower than a first determined speed threshold and/or if the second speed V2 is lower than a second determined speed threshold.

Abstract: The invention relates to an electrical machine comprising a stator (1) and a rotor (2) designed to be rotated in relation to each other, said rotor (2) or said stator comprising a plurality of permanent magnets (5), at least one permanent magnet comprising at least one fluid-propagation channel (10) extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.

Abstract: The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members (18) of a turbomachine (10), the members (18) being configured to travel over an operating area comprising a first position P1 and a second position P2, the method comprising the steps of: -(E23) determining a first pivoting speed V1 from the first position P1 to the second position P2; -(E25) determining a second pivoting speed from the second position P2 to the first position P1; and -(E26) determining an anomaly in the operation of the system for positioning the members (18) if the first speed V1 is lower than a first determined speed threshold and/or if the second speed V2 is lower than a second determined speed threshold.

Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.

Abstract: The invention relates to an electrical machine comprising a stator (1) and a rotor (2) designed to be rotated in relation to each other, said rotor (2) or said stator comprising a plurality of permanent magnets (5), at least one permanent magnet comprising at least one fluid-propagation channel (10) extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.

Abstract: A fluid valve for a hydraulic circuit of an aircraft includes a valve body with an inlet and two outlets. The valve further includes a solenoid electric actuator with a ferromagnetic mobile driver and a valve member having a ferromagnetic portion/ The valve member is movable within the valve body along a main direction and has first and second ends that define first and second cavities, respectively, on opposite sides of the valve member. A longitudinal cavity extends through the valve member parallel to the main direction and opens into the second cavity. Relative displacement between the mobile driver and the valve member modifies a communication between the longitudinal cavity and the first cavity via a side opening that is perpendicular to the main direction.

Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.

Abstract: The invention relates to a method for producing a module having an electronic chip including metallizations which are accessible from a first side of the metallizations and an integrated circuit chip which is arranged on the second side of the metallizations, opposite the first side. The method comprises the step of forming electrical interconnection elements which are separate from the metallizations, directly connecting the chip, and are arranged on the second side of the metallizations. The invention also relates to a module corresponding to the method and to a device comprising said module.

Abstract: The invention relates to a method for producing a module having an electronic chip including metallisations which are accessible from a first side of the metallisations and an integrated circuit chip which is arranged on the second side of the metallisations, opposite the first side. The method comprises the step of forming electrical interconnection elements which are separate from the metallisations, directly connecting the chip, and are arranged on the second side of the metallisations. The invention also relates to a module corresponding to the method and to a device comprising said module.

Abstract: A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine.

Abstract: A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine.

Abstract: An overspeed protection device includes at least one torque measurement unit supported by an output shaft coupled mechanically to a free turbine of a turbine engine and a signal processing unit able to transmit to a turbine engine regulating system a command to reduce a flow of fuel injected if it is detected that the torque has dropped below a first datum value. The signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger the reduction being taken during a rotation corresponding to a fraction of a revolution of the output shaft.

Abstract: Apparatus for continuous casting of metal bars, in which the metal bar is formed in a cooled mould, extracted therefrom by roller trains, cooled during extraction and along its path of extraction the metal bar is subjected to the action of the fluid in an airtight chamber, the fluid having a pressure such as to compensate the hydrostatic internal pressure in the metal bar to reduce pressure and stress on the roller trains.