Abstract: The invention relates to a method for regulating an acceleration of a turbomachine, the turbomachine comprising a combustion chamber, a high-pressure turbine located downstream of the combustion chamber and which drives a high-pressure shaft in rotation, and a low-pressure turbine located downstream of the high-pressure turbine and which drives a low-pressure shaft in rotation, characterized in that the method comprises the following steps: injecting mechanical power onto the high-pressure shaft until a speed of the high-pressure shaft attains a target value, then extracting mechanical power from the high-pressure shaft so as to maintain the speed at the target value.

Abstract: Described are supports for holding a portable electronic device. The support includes a body having an upper pivot location and a lower pivot location relative to a passenger seat back, a support structure coupled to the body, and a plurality of projections extending from a surface of the support structure. Each projection is shaped to receive a lower edge of a portable electronic device and secure the portable electronic device to the body when the portable electronic device is received by the plurality of projections.

Abstract: A device for depositing a thick metal nitride on a sample by supercritical fluids includes a first enclosure forming a first closed volume; a second enclosure placed in the first enclosure and delimited by internal walls transparent to electromagnetic radiation forming a second closed volume intended to include fluid under supercritical conditions; a heat transfer dielectric fluid circulating in the first volume around the second enclosure; a sample holder present in the second volume; an induction heating device surrounding the second enclosure; inlets for introducing a fluid and at least one precursor material into the second enclosure, and an outlet to purge the second volume.

Abstract: A baggage bar assembly may be provided for a passenger seat such as but not limited to an aircraft passenger seat. The baggage bar assembly includes a baggage bar and a support for supporting the baggage bar relative to the passenger seat. The support of the baggage bar assembly also allows for movement of the baggage bar relative to the passenger seat.

Abstract: A method for chemically pickling a cast metal part, including a metal envelope which delimits an inner space in which at least one porous ceramic core is housed, and an outer space, the ceramic core being in fluid communication with the outer space, which method including: filling the pores of the ceramic core with a liquid; and then chemically pickling the cast metal part. This chemical pickling method may be implemented in a method for manufacturing a metal part by investment casting. This method is applicable at least to manufacture of turbine blades for turbomachines and, especially, for aircraft turbojet engines.

Abstract: An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.

Abstract: A tool for manufacturing a ceramic matrix composite part by injecting a slurry, the tool includes an injection chamber intended to receive at least one fibrous preform to be densified, wherein the injection chamber includes first injection ports which are formed in a first side of the injection chamber for injecting the slurry into the injection chamber, the first injection ports being distributed along the first side of the injection chamber; the injection chamber includes first drainage ports which are formed on the first side of the injection chamber for draining a liquid phase of the slurry from the injection chamber, the first drainage ports being distributed along the first side of the injection chamber; and the tool includes a first filtration element which is located on the first side of the injection chamber and which is located opposite the first drainage ports.

Abstract: Described is an integrated electronic control system including keypad with a keypad connector, one or more galley inserts controllable by the keypad; and a control board couplable with the keypad and the galley insert. The control board includes a first connector configured to removably and electrically couple with the keypad connector, a second connector configured to removably and electrically couple with a galley insert connector, and a processor implementing a plurality of control functions related to multiple galley inserts. The processor is configured to receive an input command related to a connected galley insert from the keypad, and generate a control signal, via a control function associated with the galley insert using the input command, to control the galley insert. Further, feedback from the galley insert is received, and based on the feedback, the keypad is configured to indicate a status of the galley insert.

Abstract: An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke. The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.

Abstract: A labyrinth-type sealing device for an aircraft turbomachine includes a rotor with at least one external annular lip. The device further includes a stator with an annular coating made of abradable material with extends around the lip and which is configured to cooperate in operation with the lip in order to form a labyrinth-type seal with respect to a flow of gas flowing through the rotor axially from upstream to downstream. The coating has an internal cylindrical surface that extends around the lip and is configured to contact the lip in order to form, by friction, an annular groove, and, upstream of the lip, a preformed annular slot.

Abstract: A mechanical roller bearing comprising two bearing races each having a rolling track, rolling elements arranged between the races, the rolling elements being able to roll against a portion of the rolling tracks, the rolling elements being made of a defined material, wherein it includes a plurality of intermediate blocks arranged between the races, the intermediate blocks being made of a material having a greater stiffness than the stiffness of the material of the rolling elements in directions normal to the rolling tracks, and, when the bearing is subjected to loading below a threshold load, the intermediate blocks have a smaller dimension than the rolling elements in directions normal to the rolling tracks, the races having a greater stiffness than the rolling elements.

Abstract: Electrical cut-off device including a fuse used to open a power line in which a direct current circulates, a movable drawer connected to the fuse and capable, once the fuse is broken, of moving in a fixed chamber under the action of a compression spring mounted between the fixed chamber and the movable drawer, and an auxiliary contact whose fixed contact part is secured to the fixed chamber and movable contact part is secured to the movable drawer whose movement will cause the opening of the normally closed auxiliary contact.

Abstract: A method including at least two turbomachines disposed on either side of a main axis of the aircraft, the turbomachines each including a low-pressure shaft and a set of at least three sensors for controlling the operation of the turbomachine. The method including the following steps: for each turbomachine, acquiring the data of the set of at least three sensors, for each turbomachine, normalizing the first pressure with respect to the speed of the low-pressure shaft and with respect to the second pressure, comparing the normalized first pressure of a turbomachine with the normalized first pressure of the at least one other turbomachine of the aircraft, detecting the presence of a crosswind based on the result of the comparison.

Abstract: Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.

Abstract: An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.

Abstract: A method for treating an internal defect in a part made of a material, involves: a) detecting and locating the internal defect in the part; b) defining, inside the part, at least one target volume which at least partially includes the defect; c) for each target volume, simultaneously irradiating the target volume by at least two beams which converge in the target volume and are continuous, whereby a treated area is obtained. The energy applied to the target volume by each beam is less than a threshold energy for sintering the material, and the sum of the energies applied to the target volume by each of the beams is greater than or equal to a transformation threshold energy that corresponds to the threshold energy for sintering or melting the material; the material of the part is partially transparent to said beams.

Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.

Abstract: A constant volume combustion system for a turbomachine comprises a plurality of combustion chambers distributed annularly about an axis, each combustion chamber comprising an inlet orifice and an outlet orifice, a selective shut-off element movable in rotation relative to the combustion chambers, the selective shut-off element comprising a shroud facing the inlet and outlet orifices of the combustion chambers. The shroud including on a first annular portion at least one intake aperture intended to cooperate with the inlet orifice of each combustion chamber during the rotation of the selective shut-off element and on a second annular portion at least one exhaust aperture intended to cooperate with the outlet orifice of each combustion chamber during the rotation of the selective shut-off element. Each combustion chamber comprises a fuel injection device whose opening and closing are synchronized by the shut-off element.

Abstract: A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.

Abstract: A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).