Abstract: A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.

Abstract: Described is a passenger seat having a seat member moveable between a stowed position and a deployed position and at least one actuator coupled to at least one portion of the seat member, wherein the at least one actuator is activable without direct contact with a passenger's hand to change a lock state of the seat member, and wherein an unlocked state of the seat member permits movement of the seat member between the stowed position and the deployed position.

Abstract: The invention relates to a turbine blade (33) for a movable wheel of a low-pressure turbine of an aeronautical propulsion system, comprising a root (331), a shroud (334), and an aerodynamically profiled airfoil (333) extending from the root (331) to the shroud (334), wherein a parameter N2S is defined as: N ? 2 ? S = ? ? ( R ? e 2 - Ri 2 ) × w 2 , where: Re is an outer flowpath radius, Ri is an inner flowpath radius, w is a limit rotation speed of the drive shaft, wherein the outer flowpath radius Re and the inner flowpath radius Ri are chosen such that N2S is greater than a certain threshold which depends on the temperature T measured when the drive shaft rotates at the limit rotation speed w.

Abstract: A cooling system for a drive device with several electric machines, the cooling system including a hydraulic circuit for a coolant including a cooling part in a gearbox of the drive device for cooling the gearbox, and an air/coolant heat exchanger including cooling walls forming channels for circulating coolant for the cooling thereof, an air cooling circuit including a plurality of fans, rotationally coupled to the gearbox, a cooling part between the cooling walls of the air/liquid heat exchanger, wherein the air sucked in and propelled by the fans circulates by sweeping over the cooling walls in order to cool them.

Abstract: An unducted rectifier for a turbomachine is provided. The rectifier includes: (1) stator vanes each having a root and a blade radially projecting from the root, the root having two half-platforms; (2) pivots, each associated with a vane mounted so as to pivot about a pitch axis and configured to connect to a system for changing the pitch of the blades, each pivot having an upper platform and a cylindrical lower portion; and (3) attachment systems for attaching the half-platforms of the root of the vane to the associated pivot, each having two plates having a substantially identical shape to each half-platform and a clamping system for clamping the half-platforms between the plates of the attachment system and the upper platform of the pivot.

Abstract: The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

Abstract: Disclosed is an assembly for a turbomachine comprising: ?—a second connection element (8) having a third end (81) which is connected to a turbine shaft (2) and is mounted on a second bearing (5), and a fourth end (82) connected to a mechanical transmission device (6), the second connection element (8) having a second radial compliance (SR2); and ?—a third connection element (9) having a fifth end (91) fixedly mounted on a casing (1), and a sixth end (92) connected to the mechanical transmission device (6), the third connection element (9) having a third radial compliance (SR3), wherein a ratio of the first radial compliance (SR1) to the third radial compliance (SR3) is strictly lower than 10% and/or a ratio of the first radial compliance (SR1) to the second radial compliance (SR2) is strictly lower than 4%.

Abstract: The present invention relates to a method and a device for recording radiofrequency activity of artificial satellites orbiting the Earth and emitting electromagnetic signals, characterized in that the device contains an antenna for receiving an acquisition signal, a reception chain, a computer able to compute the power spectral density on at least one frequency sub-band based on the signal, a control device for pointing the line of sight of the antenna at at least one sequence of prescribed orbital positions that are successive and separate from one another.

Abstract: The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a direction (Y). A filler material (41) is located in the cavity (4) at a distance from the opening (5). A reinforcement (6), the density of which is higher than the density of the material (41), comprises a first reinforcement portion (61) located in the cavity (4) against the material (41) and a second reinforcement portion (62) for closing the opening (5) between the portions (21, 31) to form a single piece.

Abstract: A brake assembly is configured for use with a wheel in an ambient environment. The wheel includes a rim rotatably mounted to an axle. The brake assembly includes a brake stack and an actuation assembly configured to selectively apply a force to the brake stack. A cover sealingly engaged the rim to at least partially define a fluidic barrier between a brake cavity and the ambient environment. The brake stack is located within the brake cavity.

Abstract: Turbomachine including: a fan arranged along a longitudinal axis of the turbomachine, a primary duct able to channel a primary air flow from the fan through a compressor, a combustion chamber and a turbine of the turbomachine, an annular nacelle surrounding the fan so as to delimit a secondary duct able to channel a secondary air flow from the fan the temperature of which is less than that of the primary air flow of the fan, the secondary air flow extending around the primary air flow of the fan and, engine support arms arranged around the longitudinal axis between the annular nacelle and a hub which delimits the primary and secondary ducts characterized in that it also includes an electrical energy generation device mounted facing or so as to be able to be arranged facing one of the support arms.

Abstract: A gutter for recovering lubrication oil, particularly for a mechanical reducer, comprising un corps principal comprising an annular main body around a central axis, and a deflector attached to the main body and configured to allow the evacuation of the oil radially from an inner cavity of the main body toward the outside of the gutter, the deflector comprising a main sleeve disposed in the extension of the main body, and an evacuation channel configured to deflect oil from the main sleeve and having a curved shape such that a first end of the evacuation channel, communicating with the inner cavity, is tangent to the main body, and a second end of the evacuation channel is directed outward with respect to the annular main body.

Abstract: An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

Abstract: A blade includes a root to be mounted in a slot of plural slots which open out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk having an upstream surface and a downstream surface, each slot being delimited by a bottom surface, the rotor disk including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface; a shroud having a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.

Abstract: An inertial rotation sensor comprising a vibratory resonator (1) associated with at least two first transducers (2.1) connected to a first electronic processor unit (5) via an electronic multiplexer member (6) in order to operate successively in a motor mode and in a detection mode and in order to supply a first detection signal. The vibratory resonator (1) is associated with at least two second transducers (2.2) that are connected via two load amplifiers (3.1), two anti-aliasing filters (3.2), and two ADCs (3.3) to a second electronic processor unit (4) in order to operate in detection mode and to supply a second detection signal. The sensor includes an electronic hybridizing unit (20) for forming a third detection signal from the first and second detection signals.

Abstract: A method for densifying a fibrous texture made of ceramic material with a ceramic matrix used in injection equipment including a mold cavity defined between a mold and a counter-mold, the mold cavity defining an internal space, and a membrane comprising a stiffened zone, the membrane being intended to be placed between a fibrous texture present in the mold cavity and the counter-mold, and the stiffened zone of the membrane having a Young's modulus greater than 200 GPa, the method including placing a predensified fibrous texture in the mold cavity, the predensified fibrous texture having corrugations on the surface and placing the membrane on the predensified fibrous texture in such a way that the stiffened zone of the membrane is in contact with the peaks of the corrugations of the predensified fibrous texture; closing the injection equipment, and densifying.

Abstract: Disclosed is an aircraft turbine engine (10), comprising a gas generator (12) and a fan (14) arranged upstream from the gas generator (12) and configured to generate a gas inlet stream (F), part of which flows into a duct of the gas generator to form a primary stream (36), the turbine engine (10) comprising an electrical machine that is mounted coaxially downstream from the fan (14) and that comprises a rotor (62a) surrounded by a stator (62b) carried by an annular shroud (64), this shroud (64) being surrounded by a casing (40) of the gas generator that defines, with this shroud (64), a section of the flow duct for the primary stream (36), stationary vanes (42, 68) for straightening this primary stream (36) extending into this path.

Abstract: Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.

Abstract: A turbofan including a fan, at least one annular casing surrounding the fan and elements being fastened to an outer surface of the casing via a fastening assembly, the elements including a first elastic member arranged for urging the first end of the support away from the casing, and a first return member (27) arranged for resiliently urging the first end towards the casing, and a second elastic member (25) arranged for urging the second end of the support away from the casing, and a second return member (29) arranged for resiliently urging the second end towards the casing.

Abstract: A system for locating a strand including fibers of a first woven preform material, the preform including, at the surface, strands of fibers of a second material and the strand including fibers of the first material forming a tracer. The system further includes a camera; a light source emitting a non-polarized incident beam configured to be directed towards the preform; a polarizer configured to polarize the non-polarized incident beam before interacting with the preform in order to obtain a polarized incident beam; and a crossed analyzer; the first material being chosen from among glass, aramid and aluminum oxide; the second material being chosen from among carbon and silicon carbide; the camera being configured to film a reflected beam originating from the interaction of the polarized incident beam with the preform, the reflected beam having previously crossed the crossed analyzer, so as to locate the tracer of the preform.