Abstract: In order to fill a reservoir while avoiding laborious manual filling operations, there is added to the existing device, including a supply duct, a pump and a measuring probe, a stop valve designed to interrupt the filling as soon as the desired level has been reached, which is detected for example by an air intake which controls the closure of the valve. Two level indicators are added and make it possible to ascertain either that optimum filling has been achieved or that a malfunction is present in the system. Application to the systems for oil filling of aircraft engine reservoirs from another reservoir arranged within the aircraft, generally common to all the engines.

Abstract: A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

Abstract: An actuating device of a pump of a fuel pumping system of an engine, including a motor, a generator, an inverter, a switching member and a control member, the motor including a first rotor coupled to the pump and a first stator including at least one input stator winding, the generator including a second rotor coupled to a drive shaft of the engine, and a second stator including at least one output stator winding, the control member being configured to control the switching member in order to selectively connect each input stator winding: to a corresponding output stator winding if a speed of the engine is higher than or equal to a predetermined speed; to a corresponding output of the inverter, otherwise.

Abstract: In an electromechanical actuation chain for controlling the movement of mobile loads of an aircraft turbine engine, from a control unit, one or more of these mobile loads being actuated by an electromechanical actuator, there is provided for control of this movement a single Ethernet controller having deterministic control that uses an Ethernet bus to control a set of converters acting selectively on the electromechanical actuators.

Abstract: The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: An evaluation of the oil level of an aircraft engine tank from doses of oil delivered from another tank by a pump can be checked by comparing the evaluation of the volume provided by a sensor associated with the engine tank with an estimation of the volume extracted from the aircraft rank, either by another level sensor associated with this tank, or directly from the control of the pump. This comparison is made by a module capable of notifying staff of the need to check or maintain the device, and in particular to check if the sensor is operating correctly. Application to aeronautics, in particular to devices wherein a single aircraft tank supplies all the engine tanks.

Abstract: A power distribution device between an electric starter of a turbomachine and an electric machine toward a shaft of the turbomachine, including the electric starter, the electric machine, and a controller for controlling the electric machine. An epicyclic train reducer includes a first element intended to be coupled to the shaft, a second element coupled to the electric starter, and a third element intended to be rotated by the electric machine. The controller is configured to rotate the third of the three elements so as to obtain two bearings of reduction ratios of the speeds between the first of said three elements and the second of the three elements. The controller is configured to drive the torque of the third of the three elements in accordance with a determined output torque.

Abstract: A turbomachine comprising a cone positioned at an upstream end and secured in rotation to the low-pressure shaft, a system for deicing said cone, comprising resistive heating elements positioned in the cone, an energy transfer system, an electrical power source coupled to the high-pressure shaft and connected to the energy transfer system by a set of switches, and a computer configured so as to define a power set point for deicing the cone depending on ambient temperature and pressure data, and on an operating speed of the low-pressure shaft, and, depending on the electrical power supplied by the electrical power source, define a duty cycle of the set of switches to deliver electrical power to the resistive heating elements.

Abstract: In order to fill a reservoir while avoiding laborious manual filling operations, there is added to the existing device, including a supply duct, a pump and a measuring probe, a stop valve designed to interrupt the filling as soon as the desired level has been reached, which is detected for example by an air intake which controls the closure of the valve. Two level indicators are added and make it possible to ascertain either that optimum filling has been achieved or that a malfunction is present in the system. Application to the systems for oil filling of aircraft engine reservoirs from another reservoir arranged within the aircraft, generally common to all the engines.

Abstract: The invention relates to a method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine, the method comprising the following steps: —a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis (X) and in a second opposite direction of rotation in an alternating manner; and —a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

Abstract: The invention concerns a bypass turbomachine (1) with a primary flow path and a secondary flow path, comprising: —a low-pressure body comprising a low-pressure compressor (120) connected to a low-pressure turbine (122) via a low-pressure shaft (124), —a high-pressure body comprising a high-pressure compressor (130) connected to a high pressure turbine (132), via a high-pressure shaft (134), —a low-pressure power take-off system (220) comprising an electrical generator (226), configured to take power (W12) from the low-pressure body, wherein—the turbomachine comprises a debris removal system (500), located between the two compressors (226, 236), —the low-pressure power take-off system (220) is configured to take power (W12) from the low-pressure shaft (124) using the resistive torque of the electrical generator (226), in order to avoid a risk of surging.

Abstract: A method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine. The method includes the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

Abstract: An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

Abstract: The invention relates to a method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine, the method comprising the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis (X) and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

Abstract: A power distribution device between an electric starter of a turbomachine and an electric machine toward a shaft of the turbomachine, including the electric starter, the electric machine, and a controller for controlling the electric machine. An epicyclic train reducer includes a first element intended to be coupled to the shaft, a second element coupled to the electric starter, and a third element intended to be rotated by the electric machine. The controller is configured to rotate the third of the three elements so as to obtain two bearings of reduction ratios of the speeds between the first of said three elements and the second of the three elements. The controller is configured to drive the torque of the third of the three elements in accordance with a determined output torque.

Abstract: An evaluation of the oil level of an aircraft engine tank from doses of oil delivered from another tank by a pump can be checked by comparing the evaluation of the volume provided by a sensor associated with the engine tank with an estimation of the volume extracted from the aircraft rank, either by another level sensor associated with this tank, or directly from the control of the pump. This comparison is made by a module capable of notifying staff of the need to check or maintain the device, and in particular to check if the sensor is operating correctly. Application to aeronautics, in particular to devices wherein a single aircraft tank supplies all the engine tanks.

Abstract: A turbine engine equipped with an electrical apparatus with rotor and an epicyclic reduction gear train, includes a sun gear driven by a drive shaft about an axis of rotation, a ring gear surrounding the sun gear and configured to drive a fan shaft about the axis, and an annular row of planet gears interposed between the sun gear and the ring gear and held by a planet carrier fixed to a stator housing of the turbine engine. The stator of the electrical apparatus is fixed to the stator housing with an annular member for apparatus support. The annular member includes elongate legs that axially traverse the reduction gear. The annular member includes a first annular element for fixing to an annular flange integral with the stator housing. The stator of the apparatus has a first annular fixing flange connected integrally to opposed longitudinal extremities of the legs of the annular member.

Abstract: A turbine engine, comprising at least one drive shaft having an axis of rotation A and configured to drive a fan wheel by means of an epicyclic reduction gear train, said reduction gear having: a sun gear configured to be driven by said drive shaft about said axis A, a ring gear surrounding the sun gear and configured to drive a fan shaft about said axis A, and an annular row of planet gears interposed between the sun gear and the ring gear and held by a planet carrier fixed to a stator housing of the turbine engine, said turbine engine also having an electrical apparatus with rotor, wherein the stator of the electrical apparatus is fixed to the stator housing by means of an annular member for apparatus support, the annular member comprising legs of an elongated shape that axially traverse the reduction gear, the annular member comprising at longitudinal extremities of the legs a first annular element for fixing to an annular flange integral with the stator housing, and wherein the stator of the apparatus