Abstract: The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nose (31) comprises, at least on the metal part (27b) of the blade tip, a recess (4) of longitudinally tapering thickness (AX), delimiting on the metal part (27b) over a height (H) at least one metal projection (5) with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (27b), the recess (4) and the metal projection (5) with prescribed wear extending the first metal fin (32) and/or the second metal fin (33) and/or the upstream edge (22) of the body (20) made of composite material.

Abstract: A rotary assembly for a turbomachine including a rotor including at least two consecutive rotor stages provided with a plurality of blades and an annular rotor shroud connecting the two consecutive rotor stages, a stator including: at least one stator stage provided between the two consecutive rotor stages including a plurality of vanes, a turbomachine stator vane root, an annular clamping part and an annular support of abradable material, the root extending radially and being clamped axially between the annular support of abradable material and the annular clamping part, A space separates a radially internal end of the root and the annular support of abradable material. A turbojet engine including a rotary assembly as previously.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

Abstract: A lubricating oil distributor for a mechanical reduction gear of a turbomachine, in particular of an aircraft, includes a body of generally annular shape around an axis X and includes first and second independent oil circuits. The first oil circuit has a first oil inlet connected by a first chamber to several oil outlets distributed on the body around the axis X. The second oil circuit has a second oil inlet connected by a second chamber to several oil outlets distributed on the body around the axis X. The first and second chambers extend circumferentially around the axis X at different diameters, wherein the first and second oil circuits are formed in the body and are respectively a recovery circuit and an oil supply circuit for toothing of the reduction gear.

Abstract: A method of detecting an operation to spoof a first positioning device carried by a first vehicle moving in a zone in which at least one second vehicle carrying a second positioning device is also moving, the method comprising the step of causing at least one first positioning value to be calculated for each vehicle from initial satellite signals received by each device; the method being characterized in that it further comprises the steps of: causing the second device to initiate a latching stage in order to make a new search for satellite signals and using the new satellite signals received by the second device to calculate a second positioning value for the second vehicle at the same instant as the first value; comparing the first and second values relating to the second vehicle; and issuing a warning when the two values do not coincide.

Abstract: Described are tray table tuning mechanisms for a passenger seat. The tray table tuning mechanisms can include a pivot limiting member, a paddle arm deployment member, an adjustment plate, and a paddle arm. The paddle arm deployment member and the adjustment plate may be pivoted relative to the pivot limiting member. The paddle arm can include at least one stop member and may be pivotably coupled to the paddle arm deployment member. Additionally, the paddle arm may be pivoted between a stowed state and a deployed state. In the deployed state, the stop member can abut a portion of the adjustment plate to limit rotation of the paddle arm deployment member in a first direction.

Abstract: A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.

Abstract: A metal part with a wall thickness less than 5 mm includes a preform made from a flexible composite sheet, a flexible composite sheet segment, and an appended insert including a fastening portion that is sandwiched between a rear end of the preform and the flexible composite sheet segment. The flexible composite sheet segment encloses the fastening portion of the appended insert.

Abstract: The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

Abstract: Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.

Abstract: An aircraft wheel includes a rim that is secured to a central hub defining an axis of rotation of the wheel. The wheel includes one or more driving pins that extend from the hub, projecting in a direction substantially parallel to the axis of rotation of the wheel so as to cooperate with a driving member for driving the wheel in rotation. The driving pin is distinct from bolts assembling together parts of the wheel.

Abstract: A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.

Abstract: A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.

Abstract: An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.

Abstract: A method for dating images obtained by at least one camera equipping a vehicle includes acquiring a reference signal including time information and generating a modulated signal in response to the reference signal. The modulated signal has at least one retiming pulse with a retiming period which that is different from a base period of the modulated signal. The method further includes, for each camera acquiring images at a frequency depending on the frequency of the modulated signal, each image being associated with a timestamp provided by the camera, and determining the time difference between the timestamps of two successive images of the camera. If the time difference determined between said timestamps is different from the base period of the modulated signal, the method assigns a reference date to said images depending on the time information of the reference signal.

Abstract: An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

Abstract: A method for manufacturing a metal component includes the following steps: a shell made of a titanium-based material is provided, the shell having a first surface and a second surface remote from the first surface; a covering layer made of a titanium fire-resistant material is produced by additive manufacturing on the shell such that the covering layer at least partially covers the first surface and/or the second surface; and, after the additive manufacturing step, the metal component is heat treated at a temperature of between 200° C. and 1000° C.

Abstract: The invention relates to a method for controlling a three-phase inverter (3) using a 120° control arrangement associated with a PWM-type control, the inverter (3) being driven by a controller and configured to power a permanent-magnet synchronous motor (5) of a device on board an aircraft. The motor (5) comprises a stator and a rotor that can be rotated relative to the stator when the motor (5) is powered. The inverter (3) comprises three branches (31, 32, 33), each branch comprising two switches (310, 311, 320, 321 and 330, 331) associated with a motor winding sing a 120° control arrangement of a three-phase inverter. The method is characterised in that when one switch on one branch is controlled such as to switch front the on-state to the off-state, the other switch on said branch is controlled such as to be in the on-state for a sufficient amount of time to allow the magnetic discharge of the motor winding associated with said branch.

Abstract: An articulating arm assembly for a passenger seat includes a static portion attachable to the passenger seat, a rotation portion attached to the static portion such that the rotation portion is pivotable about a rotation axis, an arm body attached to the rotation portion, such that the rotation portion and the arm body are movable between a stowed position and a deployed position, and a wiring portion disposed inside the arm body and extending from the arm body into the rotation portion. The wiring portion extends parallel to the rotation axis from the rotation portion toward and into the static portion.