Abstract: A magnetic head for a magnetic detector for detecting metal particles in a hydraulic circuit includes an axial body internally including at least one magnet, at least a first electrode defining an air gap zone located in the magnetic field created by the magnet, such that the circuit creates a particle alignment zone in the air gap, and an electrical connector for electrically connecting the electrodes. The magnet can be a diametrically magnetized magnet.

Abstract: An internal gear pump comprising: a ring with internal teeth delimiting a cavity and a gear disposed in the cavity, the gear comprising external teeth cooperating with the internal teeth to drive the ring in rotation, remarkable in that it comprises a pinion disposed in the cavity and driving the gear in rotation. The pinion cooperates with the external toothing of the gear. In an alternative embodiment, the gear comprises an internal toothing which cooperates with the pinion.

Abstract: A multispectral harmonisation device intended to align the optical channels of an optronic system that includes at least two directional optical sources emitting respective optical beams of various wavelengths belonging to various spectral bands and comprises a parabolic mirror and means for positioning and orienting each of the optical sources so that each of the optical beams emitted by the optical sources passes through the optical focus of the parabolic mirror before being reflected by said parabolic mirror so that all the optical beams form, by reflection on the parabolic mirror, a multispectral collimated beam.

Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap including respective ducts for circulation of cooling air connected to one another to allow cooling of each of the flaps. The duct of the divergent flap includes an impingement cooling cavity defined by two walls of lateral ends provided with air passage orifices through which the impingement cooling cavity opens towards the outside.

Abstract: An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.

Abstract: The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.

Abstract: Electrical power supply circuit for a power module comprising an electrical transformer, a first substrate having a first side including a heat sink and a second side, a second substrate having a first side including a heat sink and a second side, first metal tracks disposed on the second side of the first substrate, second metal tracks disposed on the second side of the second substrate, electrical connectors disposed between the first and second substrates to electrically connect a first metal track to a second metal track, the primary circuit of the electrical transformer comprising a first part of the first metal tracks and a first part of the second metal tracks, and the secondary circuit of the electrical transformer comprising a second part of the first metal tracks and a second part of the second metal tracks.

Abstract: A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.

Abstract: A composite material blade for a fan of a turbine engine, includes a first portion that extends to the root of the blade and that is made of a first material including first fiber reinforcement densified by a first matrix, the blade also including a second portion that extends to the tip of the blade and that is made of a second material that is different from the first material and that includes second fiber reinforcement densified by a second matrix, the second material possessing abrasion resistance that is less than that of the first material.

Abstract: A method for separating a first mechanical part from a second mechanical part is described, wherein the second mechanical part is bonded to the first mechanical part by an adhesive film along a connecting area, the first mechanical part having a first specific thermal conductivity and the second mechanical part having a second thermal conductivity that is higher than the first thermal conductivity. The method includes at least one cooling step during which the second mechanical part is cooled to a negative temperature and at least one stressing step during which the second mechanical part is subjected to mechanical stress in order to cause the adhesive film to break.

Abstract: Lubricating oil distributor for a mechanical reduction gear of a turbine engine, in particular of an aircraft, wherein it has a general annular shape around an axis X and is formed of a single part, the distributor including first and second independent oil circuits, the first oil circuit including a first oil inlet connected by a first annular chamber to several oil outlets, and the second oil circuit including a second oil inlet connected by a second annular chamber to several oil outlets, the first chamber including a section that is at least partially nested in a section of the second chamber.

Abstract: The field of integrated health monitoring using Bragg grating optical fibre sensors including a sensor and methods for locating and installing this sensor on a support. The Bragg grating optical fibre sensor includes an optical fibre wherein at least one set of patterns forming a Bragg grating is written, the optical fibre further including a set of microstructures in the vicinity of each Bragg grating, the microstructures being separate from the patterns forming the Bragg grating, each microstructure being capable of scattering a portion of a light beam within a predetermined range of scattering wavelengths.

Abstract: A device for supplying fuel to a combustion chamber of a gas generator includes an injection wheel (14) for injecting fuel into the combustion chamber (18),—a fuel supply rail (20) including an internal fuel circuit (30) with a fuel outlet means (32) supplying fuel to an annular spray chamber (24) formed between the rail (28, 44, 48, 52, 56) and the injection wheel (14),—at least one dynamic annular seal (26) adapted to provide a seal between an annular face (34) of the fuel supply rail (28, 44, 48, 52, 56) and the injection wheel (14), wherein the internal fuel circuit (30) of the fuel supply rail includes an annular fuel flow part arranged radially at the dynamic annular seal (26).

Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Abstract: An acoustic treatment device for an aircraft turbojet engine nacelle forms an annular ring including several sections, each section having a sound absorption structure, an outer skin and two lateral skins attached to the inner air inlet shroud of such a nacelle by fasteners, and the sections being connected to each other by battens.

Abstract: Systems and techniques for engine starter control may include determining a current speed band associated with an engine start for a current time increment, determining a previous speed band associated with the engine start for a previous time increment within the engine start, receiving a measured current value, determining a target current value based on the current speed band, the previous speed band, whether an acceleration or deceleration occurred between the current speed band and the previous speed band, and a mode of a system for engine starter control, and adjusting a current for the engine start based on the target current value.

Abstract: A flexible coupling for coupling a first shaft and a second shaft includes a first body and a second body. The first body includes a first end to be fixed to the first shaft, a second end to be fixed to the second shaft and a first tooth, fixed to the radially inner face. The second body is secured to the first body, and has a radially outer face and a second tooth fixed to the radially outer face. The first tooth and the second tooth come into contact when a torque is applied to the first end of the first body so as to transmit the torque to the second end of the first body by the intermediary of the second body.

Abstract: A power conversion system for an aircraft on-board power system converts high voltage DC to low voltage DC and vice versa. The system includes switching means configured so that the system operates in a plurality of configurations, each forming an isolated DC/DC converter.

Abstract: A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longit