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.

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 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: 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: 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: 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 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: The invention relates to a fuel cell (1) comprising a stack (2) comprising a plurality of cells and a plurality of fluid flow shafts, two end plates (3) and a plurality of traction members, at least one end plate (3) has a main device (5) having at least one access opening (51) aligned with a flow shaft and at least one main traction member (T1) configured to apply a main compression to a main body so as to urge the main body (50) against the stack (2) at the flow shaft, and an auxiliary device (6) configured to urge an auxiliary body against the stack (2), the auxiliary compression being applied at a distance from the flow shaft of the stack (2), the main device (5) being mounted removably with respect to the auxiliary device (6).

Abstract: A distributor for a turbine of a turbomachine. The distributor includes a radially inner platform, a blade and a root which is coated with a track made of an abradable material. According to the invention, the distributor includes a leakage gas reintroduction duct. The duct includes an inlet through the track made of an abradable material, an outlet opening through a downstream surface of the root, and a duct intermediate portion which extends from the inlet up to the outlet. The duct intermediate portion is orientated with a tangential component.

Abstract: A tray table tuning mechanism having a mount member; a pivot limiting member coupled to the mount member and having a mating surface defining a groove; a paddle arm deployment member pivotably coupled to the mount member and pivotable relative to the pivot limiting member; and a paddle arm pivotably coupled to the paddle arm deployment member, pivotable between a stowed state and a deployed state, and having at least one stop member; wherein, in the deployed state of the paddle arm, the at least one stop member is positioned within the groove and mates with the mating surface.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including a hydraulic actuator capable of rotating about the longitudinal axis and configured to rotate the vanes about their pitch axes, a pump for supplying fluid to the hydraulic actuator, including a transmission shaft and a placed around the transmission shaft and rotating as one with the drive shaft, and an electric machine including a rotor rotating as one with the transmission shaft and a stator rotationally fixed relative to the longitudinal axis. The stator can be connected to a power supply cable passing through a passage provided in the third element of the speed reducing gear.

Abstract: A stator part of a turbomachine includes a platform, a blade, and a fin. The blade and the fin extend from the platform. The platform, an extrados of the blade and the fin define therebetween a gas flow channel. The channel has a section in a plane normal to an axis of the turbomachine, the section having a surface area, the surface area continuously decreasing from upstream to downstream with reference to a general gas flow direction through the turbomachine.

Abstract: A passenger seat headrest may be provided for a passenger seat such as but not limited to an aircraft passenger seat. The passenger seat headrest includes a main portion, a wing, and a hinge connecting the wing with the main portion such that the wing is movable relative to the main portion about at least one axis. The hinge is adjustable such that a resistance to rotation of the wing relative to the main portion is adjustable.

Abstract: Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.

Abstract: A portable electronic device holder for a passenger seat includes a base plate, a back plate pivotally attached to the base plate, and at least one movable arm attached to the back plate. The back plate may be adjustable relative to the base plate over a range of approximately 0° to 90°.

Abstract: A structural shroud assembly for a passenger seat includes a structural shroud having a first end, a second end opposite from the first end, and a central cavity between the first end and the second end. An armrest pivot may be supported at the first end of the structural shroud. In some cases, the structural shroud may be an armrest. In other cases, the structural shroud is an upper spreader for the passenger seat configured to support a seat back of the passenger seat, and a lower spreader configured to receive at least one seat beam tube is attached to the upper spreader.

Abstract: An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.

Abstract: A detachable device for closing a space inside an airplane includes: a frame comprising at least one upright, the frame comprising at least one attachment interface with a structural element, a curtain assembly comprising a flexible curtain, a roller around which the flexible curtain can be wound, and at least one guide device comprising an electric-motor actuator, the guide device-being capable of translationally guiding the flexible curtain relative to the upright such that the flexible curtain can be moved in a direction of movement parallel to a longitudinal direction of the upright between a stowed position in which the flexible curtain is mainly wound around the roller and an extended position in which the flexible curtain is mainly unwound relative to the roller.

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: A seat back assembly for a passenger seat, such as but not limited to an aircraft passenger seat, includes a seat back and a backrest assembly. The backrest assembly includes a backrest and a headrest. The backrest is movable relative to the seat back between a stowed position and a deployed position. The headrest is supported on the backrest and is movable relative to the backrest between a stowed position and a deployed position.