Abstract: An accessory gearbox for a turbomachine, the gearbox being equipped with a pump and including intermeshing pinions, one of which is formed as a single piece with a coaxial shank for driving a rotary part of the pump, wherein said rotary part is directly mounted on the shank.

Abstract: The invention concerns a planet carrier (5) for an epicyclic speed reduction gear, comprising an annular cage (7) comprising two sides (9, 10) extending radially, linked by bridges (16), seats (6) extending axially between the sides (9, 10) and being intended to support planet gears mounted rotating about the seats (6). One (9) of the sides (9, 10) of the cage (7) is immovably fixed to a torque output member (8), in such a way as to form a single structural assembly.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces.

Abstract: A three-phase/two-phase rotary transformer includes a first single-phase rotary transformer and a second single-phase rotary transformer the first transformer including a first body defining a first slot, a first coil in the first slot, a second body defining a second slot, and a second coil in the second slot the second transformer including a third body defining a third slot, a third coil in the third slot, a fourth body defining a fourth slot, and a fourth coil in the fourth slot, wherein one terminal of the first coil is connected to the midpoint of the third coil, said the first body the first coil the third body, and said the third coil forming a three-phase portion of the transformer the second body the second coil the fourth body, and said fourth coil forming a two-phase portion of the transformer.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including a device forming a fluid circulation passage configured to generate a pressure drop, created by stacking at least two elements. Each element includes a passage for carrying fluid configured to generate a pressure drop and including an inlet and an outlet. The outlet, or inlet, of the passage of one of the elements is, respectively, connected to the inlet, or to the outlet, of the passage of the other element.

Abstract: A three-phase transformer including a primary portion and a secondary portion, the primary portion including a first body made of ferromagnetic material and primary coils, the secondary portion including a second body made of ferromagnetic material and secondary coils, the first body defining a first annular slot of axis A and a second annular slot of axis A, the primary coils including a first toroidal coil of axis A in the first slot, a second toroidal coil of axis A in the second slot, and one or more third toroidal coils connected in series, the third coils being wound around one of the legs, and passing via slots in the leg.

Abstract: An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power.

Abstract: A three-phase-two-phase transformer including a magnetic circuit, three-phase windings, and two-phase windings, wherein the magnetic circuit includes a first column, a second column, and a third column that are magnetically connected together, the three-phase windings including a first winding, a second winding, and a third winding. The two-phase windings include a fourth winding around the first column, a fifth winding around the first column, a sixth winding around the third column, and a seventh winding around the third column, the fourth winding and the seventh winding being connected in series and forming a first two-phase phase, and the fifth winding and the sixth winding being connected in series and forming a second two-phase phase.

Abstract: The invention relates to a power transmission system, in particular for a turbine engine such as an airplane turboprop or turbojet, the system comprising a transmission shaft (40) connected to a drive shaft (31) by connection means (30), such as bevel gears, and that drive equipment or accessories. The transmission shaft (40) is designed to operate under supercritical conditions and includes damper means for damping vibration at its resonant speed.

Abstract: A method of controlling a permanent magnet synchronous machine including a stator and a rotor. The method includes determining an estimated position of the rotor, and determining a second in-phase voltage setpoint that, in alternation, is equal either to a first in-phase voltage setpoint or else to the first in-phase voltage setpoint plus a predetermined periodic signal. The determining an estimated position of the rotor includes determining a coupling term, determining a speed of rotation of the rotor as a function of the coupling term, and determining the estimated position of the rotor by integrating the speed of rotation of the rotor.

Abstract: A power supply circuit for supplying electrical energy in an aircraft, the circuit including a power supply generator configured to be driven in rotation by the engine of the aircraft to power electrical equipment of the aircraft engine. The power supply generator includes an asynchronous machine connected to an excitation device. The asynchronous machine includes a rotor configured to be driven in rotation by the engine and a stator connected to the electrical equipment. The excitation device is configured to cause a reactive current of flow in the stator.

Abstract: A turbine engine starter-generator including a main electrical machine including a stator and rotor with a wound rotor inducer and damper bars forming a cage, and an exciter including a stator inducer and rotor with rotor windings connected to the rotor inducer of the main electrical machine via a rotary rectifier. During a first starting stage, the electrical machine operates in asynchronous motor mode by injecting AC into its stator windings, a starting torque being generated by the damper bars, without the rotor inducer of the main electrical machine contributing significantly to generating starting torque. Then in a second starting stage, the main electrical machine operates in synchronous motor mode by injecting AC into its stator windings, while feeding its rotor inducer with DC via the exciter, the change from the first stage to the second stage taking place when rotation speed of the shaft reaches a predetermined value.

Abstract: An accessory relay for a turbine engine, including a housing in which at least one gear wheel is installed for mechanically driving an accessory mounted on the housing, the gear of the wheel being driven via an input shaft supplying torque required for the mechanical drive, the shaft of the wheel being supported by at least two ball or roller bearings, and passing through at least one of the walls of the housing via an opening positioned opposite the accessory and closed by a first accessory cover attached onto the housing, wherein, for at least one of the gear wheels, the shaft thereof passes through two walls of the housing via openings closed by covers attached onto the housing, and the outer races of the two bearings are supported by the covers.

Abstract: An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Abstract: An accessory gearbox for a gas turbine, the gearbox including a front lateral face and a rear lateral face opposite from the front face and a peripheral rim closing the box, and at least one mounted gear train including a plurality of gearwheels meshing together, each gearwheel being carried by a central shaft held at each of its two ends by a respective rolling bearing, the rolling bearings of at least one of the two ends being fastened together on at least one perforated plate attached to the peripheral rim.

Abstract: A generation method performed by a generator module of an electricity network of an aircraft, the electricity network including a power supply line powered by the generator module, a DC bus powered from the power supply line via a rectifier, and at least one electrical actuator powered with AC from the DC bus via an inverter. The generation method includes: delivering an AC voltage as a function of a voltage setpoint and of a voltage measured in the on-board network; and determining the voltage setpoint as a function of an operating parameter of the actuator.

Abstract: A method for controlling a converter for converting an n-phase AC input voltage into a DC output voltage, each phase of the AC input voltage being connected to a switch of the converter. The method includes determining the signs of j characteristic voltages (Va, Vb, Vc, Va-Vb, Vb-Vc, Va-Vc, Va+20°, Vb+20°, Vc+20°, Va?20°, Vb?20°, Vc?20°); determining a reference combination (C1-C12, C1-C18), to which the signs of j characteristic voltages (Va, Vb, Vc, Va-Vb, Vb-Vc, Va-Vc, Va+20°, Vb+20°, Vc+20°, Va?20°, Vb?20°, Vc?20°) correspond, by comparing the signs of the j characteristic voltages to data from a reference table; and (c) opening each switch for an opening time (t1, t2, t3) pre-determined according to the reference combination (C1-C12, C1-C18) identified during the determining of the reference combination.

Abstract: A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.

Abstract: A power supply circuit for supplying electrical energy in an aircraft, the circuit including a power supply generator configured to be driven in rotation by the engine of the aircraft to power electrical equipment of the aircraft engine. The power supply generator includes an asynchronous machine connected to an excitation device. The asynchronous machine includes a rotor configured to be driven in rotation by the engine and a stator connected to the electrical equipment. The excitation device is configured to cause a reactive current of flow in the stator.