Abstract: The invention relates to a method which comprises the following steps: —measuring a pressure difference at terminals of a metering device (22) supplied with fuel by a pump (20); —calculating a position of a valve (24) regulating the pressure difference; —determining at least one estimated position of the valve from the pressure difference and at least one reference function giving the pressure difference as a function of the position; —calculating at least one value representing a drift of the pump (20) using the calculated position and the estimated position; and—comparing the value with a predetermined threshold.

Abstract: The present invention relates to a turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. This rotor is characterised in that each blade comprises a circumferential coupling rib, in that it comprises a plurality of platforms, which comprise a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

Abstract: A tool-electrode for machining an imprint in a conductive part by sinking-die type electrical-discharge machining. It includes a conductive body having lower and upper opposite surfaces, two opposite main lateral surfaces, lower and upper areas superposed according to a die-sinking direction of the tool-electrode, the lower area comprising the lower surface and a portion of the main lateral surfaces, the upper area including the upper surface and the other portion of the main lateral surfaces. The body is provided, at least in the lower area, with a plurality of openings selected from among channels or slots; a channel is an opening which opens onto at least one of the upper and lower surfaces; a slot is an opening which opens onto the lower surface and onto the two main lateral surfaces.

Abstract: An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.

Abstract: An aircraft passenger suite (200) and method are provided. The aircraft passenger suite comprises a console (150) and a table (130) movably mounted to the console, the table being moveable along a table path between a first position and a second position. A controller (210) controls electro-mechanical movement of the table along the table path. The controller comprises an initiation input for receiving an instruction to initiate electro-mechanical movement of the table. The suite comprises sensing equipment for sensing if any obstacle is present on the table path and providing, to the controller, an indication of whether or not any obstacle is present on the table path. The controller is configured to prevent electro-mechanical movement of the table along the table path if the controller receives an indication that an obstacle is present on the table path.

Abstract: A method for continuously manufacturing a complex acoustic multi-element panel for an acoustic attenuation structure, the method including supplying a thermoplastic resin film at the entry of a stamping system including at least one pair of complementary cylinders, a heating of the thermoplastic resin film upstream of the entry of the stamping system, and a passage of the thermoplastic resin film between the at least one pair of complementary cylinders, the pair of complementary cylinders including a male cylinder with teeth radially protruding from the cylinder and a female cylinder with cavities on its radial surface, the cavities of the female cylinder being of shapes complementary to the shapes of the teeth of the male cylinder and a separation of the stamped film at the exit of the stamping system using a separator disposed at the exit of the stamping system between the stamped film and the female cylinder.

Abstract: Described is a passenger seat having a center console. The center console has a stationary portion including: a stationary portion structural member positioned at a connecting end of the stationary portion; and a disconnect panel. The center console has a separable modular portion having: a separable modular portion structural member positioned at a connecting end of the separable modular portion and coupleable to the stationary portion structural member; and an electrical wiring consolidation device that includes: an electrical cable bundle; and an electrical connector coupleable to the disconnect panel. The stationary portion structural member, the disconnect panel, the separable modular portion structural member, and the electrical wiring consolidation device form a quick connect structure for coupling the separable modular portion with the stationary portion.

Abstract: An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.

Abstract: The invention relates to a device (2) for transferring heat from a thermally conductive plate (30) capable of capturing the heat from a zone placed on a first side (32) of the plate, the device comprising at least one fin (35) placed on a second side (34) of the plate (30) opposite the first side (32) and having a duct (36) extending in a longitudinal direction (L) between a first end (38) connected to the plate and a second end (40) opposite the first end and which opens out, the duct (36) being connected to at least one Venturi-effect neck (42) bringing cooling air into the duct, the neck (42) being formed in the vicinity of the first end of the duct and the plate (30).

Abstract: An aircraft including at least one unducted turbine engine for the propulsion of the aircraft. The turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with respect to the longitudinal axis, each stator blade being defined, in a plane transverse to the longitudinal axis, by an angular position; and at least one aerodynamic obstruction positioned close to the turbine engine. The stator of the turbine engine comprises stator blades having a first chord, referred to as conventional blades, and at least one stator blade having a second chord larger than the first chord, referred to as the elongate blade, said at least one elongate blade being positioned in an interference angular range defined opposite the aerodynamic obstacle, so as to increase the straightening of the airflow from the rotor in the interference angular range.

Abstract: The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4% aluminium, at least 3.9% molybdenum, at least 3% titanium, at most 0.5% iron, at least 0.012% boron, at most 0.060% zirconium, at most 0.150% manganese, at most 0.2% silicon, at most 0.1% copper, at most 0.5 ppm bismuth, at most 5 ppm silver, at most 5 ppm lead, at most 25 ppm sulphur, at most 200 ppm oxygen, and at most 60 ppm nitrogen.

Abstract: A filter includes a positive busbar and a negative busbar that have a positive terminal and a negative terminal, respectively; at least one positive output terminal and at least one negative output terminal, respectively; and two portions, respectively, each portion having parallel folds to define planes which succeed one another. Each plane is inclined relative to the next plane. One of the portions is an internal portion that is fitted inside the other portion, which is an external portion. Each plane of one portion extends in parallel with and facing an associated plane of the other portion. Differential mode capacitors connected between the two portions.

Abstract: A system for cooling oil in an aircraft turbine engine includes an intermediate support casing configured to be located between a low-pressure compressor and a high-pressure compressor of the aircraft turbine engine. The system further includes a heat exchanger for cooling the oil by heat exchange with air. The heat exchanger is at least partially integrated into the intermediate support casing.

Abstract: A blade for an unducted fan of a turbomachine includes an airfoil formed of plural airfoil sections that are stacked along an airfoil axis. A difference in sweeps corresponding to a difference between a leading edge sweep and a trailing edge sweep is negative, and substantially between ?30° and 0°, for any airfoil section whose height is between 10% and 30% of an airfoil height of the airfoil, and is positive, and substantially between 0° and +40°, for any airfoil section whose height is between 50% and 90% of the airfoil height.

Abstract: The present invention relates to a turbine rotor (1) comprising a rotor disc (2), provided at its periphery with a plurality of axial cells (23) for receiving a bilobed root (30) of a blade (3), each cell (23) comprising a radially inner cavity (232) and a radially outer cavity (231). This rotor is characterised in that it comprises a ring (4) for axially retaining the blade roots and an annular flange (5), the ring (4) comprising a radially inner portion provided with notches (43) and being arranged against the upstream face (21) of the disc (2), so that each of its notches (43) is located opposite a cell (23) of the disc (2), the flange (5) being secured against the upstream face of the ring (4), forming a space (E) with said disc (2), and comprising at least one air-intake opening (54) which opens into said space (E), and in that each blade (3) comprises a groove (33) for receiving the outer circumferential edge (46) of said ring (4).

Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.

Abstract: A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine, includes a blade having a vane connected to a root. A hub accommodates the root of the blade, and a ring is mounted around the root and in the hub. Stops are also mounted around the root and in the hub. A nut is threadedly engaged with a thread of the ring and is configured to bear axially against the hub to secure the assembly.

Abstract: A vane for an aircraft turbomachine includes a blade and a cooling circuit inside the blade. The cooling circuit has at least one longitudinal flow cavity of a cooling air stream (RF). The cooling circuit further includes elements that protrude into the cavity and are configured to disrupt the air stream. Each of the protruding elements is generally arc-shaped and internally defines, with a first wall, a first cross-sectional flow area, and externally, with a second wall opposite the first wall, a second cross-sectional flow area. Each of the elements is configured such that the first or second cross-sectional flow area is reduced from upstream to downstream relative to the direction of the air stream.

Abstract: A method for the tomographic analysis detects anomalies in a part. The method includes the steps of acquiring at least one three-dimensional image of the part by means of a tomography device; subdividing the image into elementary subparts; analyzing a grayscale distribution in each subpart; obtaining at least one parameter representative of said grayscale distribution for each subpart; and comparing the one or more parameters obtained for each subpart with standard values characteristic of a defect-free region. The method further includes the steps of detecting abnormal subparts for which the one or more parameters differ from the standard values; determining risk regions, which comprise each abnormal subpart and each subpart adjacent to at least one abnormal subpart; and analyzing the risk regions in order to detect the anomalies in the part.

Abstract: Analysis device for detecting solid particles in suspension in a lubricant, the analysis device comprising one or more ferromagnetic solid particle sensors, one or more other sensors able to detect non-ferromagnetic solid particles, and one or more magnets. The ferromagnetic solid particle sensors are offset in a direction perpendicular to a main direction of flow of the lubricant in relation to the other sensors, and the magnets are arranged so as to attract ferromagnetic solid particles towards the sensors of ferromagnetic solid particles by drawing them away from the other sensors.