Abstract: A turbojet engine, having a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes extending in the secondary duct downstream of a fan, at least one servo extending in the secondary duct downstream of the guide vanes and housed in a profiled casing, and at least one air sampling scoop located in the region of the casing and equipped with a control valve. Where at least one guide vane located in the vicinity of the casing has a variable geometry zone, the geometry of which can be adjusted during operation.

Abstract: The invention relates to a method for modelling the behaviour of a circular rolling mill (1) intended for rolling a cylindrical component on the basis of a setpoint, the circular rolling mill comprising at least one tapered roller (3) configured to effect a translational movement in a first direction (Y), and a mandrel (2), configured to effect a translational movement in a second direction (X), the setpoint comprising a setpoint for the rate of increase of an outside diameter of said cylindrical component as a function of said external diameter, and a setpoint for the height of the cylindrical component in the first direction as a function of a thickness of the cylindrical component in the second direction.

Abstract: Systems and methods are described herein that utilize a decentralized control panel architecture to monitor or control components or (sub-)systems of an aircraft or other vehicle. A controller can be used to receive information from multiple input sources and send a command to one or more output devices based on the received information. The received information may be of different types or formats that can be read by the controller. The controller may cause a visual or physical change to an actuator based on the command. One or more control panel entities can be communicatively coupled with the controller and used to access information about one or more (sub-)systems of the vehicle and send commands where appropriate.

Abstract: A load detection system detects loads applied to a landing gear assembly during landing. The landing gear assembly includes an axle coupled to a piston rod of a compressible shock strut and a wheel rotatably mounted the axle. A torque link includes a lower link coupled to the piston rod of the shock strut so that compression of the shock strut rotates the link about a first axis. The load detection system includes a probe rotatably coupled about a second axis. The probe engages a ground surface when the shock strut is uncompressed and the wheel contacts the ground surface. The lower link rotates the probe as the shock strut compresses. A sensor senses a position of the probe, which corresponds to a load on the wheel when the shock strut is uncompressed and the wheel is in contact with the ground surface.

Abstract: A fuel cell comprising an upper plate and a lower plate, a stack of energy cells, the stack being disposed between the upper plate and the lower plate, the stack being divided into a plurality of energy cell stages, a plurality of collectors separating each energy cell stage, three inlet vents extending from the lower plate to the upper plate, over the entire height of the stack of energy cells, the three inlet vents being configured to respectively provide the energy cells with heat transfer fluid, comburent fluid and liquid fuel, and a movable piston is disposed in each of the inlet vents, each piston being configured so that its position in the inlet vent selectively opens one or more of the fluid ducts of one or more energy cell stages, and wherein each piston is driven independently of the other pistons.

Abstract: Systems and methods are described herein for pairing wireless peripherals with networked devices. Knowledge of the location of the networked devices can be used to properly route or transmit audio to paired wireless peripherals, regardless of whether the wireless peripherals are paired with the correct networked devices provided they are networked with other potential devices. This can be accomplished by prompting users to select an input based on an audio challenge to determine which of the wireless peripherals should be mapped to which of the networked hosts.

Abstract: The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.

Abstract: An aircraft automatic braking system, comprising: a first functional module arranged in order to implement a state machine that includes a first branch comprising first states corresponding to a landing of the aircraft, a second branch comprising second states corresponding to a rejected take-off of the aircraft, and transitions, the first states, the second states and the transitions being defined independently of deceleration rates; a second functional module arranged in order to define a target deceleration of the aircraft at least on the basis of the deceleration rates and a current state of the state machine; and a third functional module arranged in order to define, at least on the basis of the current state and the target deceleration, an automatic braking command in order to control actuators of wheel brakes of the aircraft.

Abstract: A nickel-based superalloy includes, in atomic percentages, 13% to 21% chromium, 15% to 26% cobalt, 4% to 8% aluminum, 4.5% to 8% titanium, 8% to 18% iron, boron in an atomic percentage less than or equal to 0.5% or no boron, carbon in an atomic percentage less than or equal to 1% or no carbon, at least one additional element selected from molybdenum, tungsten, tantalum and niobium, a total atomic content of the at least one additional element being less than or equal to 1.5% or no such at least one additional element, the remainder being nickel and unavoidable impurities, with a sum of the atomic percentages of aluminum and titanium being comprised between 8.5% and 15%. The novel superalloy composition has a limited density and exhibiting, when hot, good mechanical properties as well as good resistance to oxidation and corrosion.

Abstract: The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.

Abstract: The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).

Abstract: Instrumentation comb for an aircraft engine including a central tube with a longitudinal axis on which a determined number of orifices spaced apart along this longitudinal axis are drilled and a base forming a proximal end of this tube and intended to be fixed on a crankcase portion of the aircraft engine, each orifice being associated with a sensor for measuring a physical parameter of the aircraft engine and the base integrates a slave processing unit connected to each of the measuring sensors by a communication link able to receive in real time digital measurement data corresponding to the physical parameters measured by the measuring sensors and intended to be communicated to a master processing unit by a single communication link.

Abstract: A motor is configured to apply a rotational force to a wheel that includes a rim rotatably mounted to an axle about a first axis. The motor has a rotor coupled to the rim. The rotor has an interior cavity and a plurality of radial slots formed therein. A cylindrical stator is disposed within the cavity and has a second axis offset from the first axis. The stator is fixed in rotation relative to the axle. The motor further includes a plurality of vanes, each vane being slidably disposed within one of the plurality of radial slots. A compressed gas source is in fluid communication with the cavity and selectively provides compressed gas to the cavity to rotate the rotor.

Abstract: A turbomachine module having a longitudinal axis, having a shroudless propeller which is rotated about the longitudinal axis by a drive shaft, which is connected at least to a compressor rotor, and at least one distributor comprising a plurality of stator vanes which extend along a radial axis which is perpendicular to the longitudinal axis Z from a fixed casing, the distributor being arranged downstream of the propeller. The fixed casing can be an inter-compressor casing which is arranged downstream of a low-pressure compressor, along the longitudinal axis, the inter-compressor casing having a ring which has a longitudinal axis and which is provided with sleeves intended to support the stator vanes, the inter-compressor casing and the ring being monobloc.

Abstract: A method and system control the thrust of an aircraft turbomachine having a high bypass ratio by direct action on a variable-pitch system. The variable-pitch system varies the pitch of the vanes of a stator of a low-pressure compressor for the open-loop control of the thrust of the turbomachine. The method also provides closed-loop control of the pitch of the blades of a propeller based on a rotational speed of the propeller.

Abstract: The invention describes a method for assessing the service life (DDV) of a turbine engine part, comprising the following steps: S1: determining average damage to the part over time (E_moy(t)) from stresses applied to the part on the basis of wear of the part (?(u)) and a law of variation in the wear of the part over time (u(t)); S3: determining cumulative damage (E_cum) to the part corresponding to damage on breaking (E_rupt) of the part, the cumulative damage (E_cum) corresponding to the integral of the average damage over time (E_moy(t)) between an initial time (t_0) and an end time (t_rupt): E_cum=E_rupt=Formula (1); and S4: inferring the service life (DDV) of the part, the service life (DDV) corresponding to the end time (t_rupt).

Abstract: A method for manufacturing a composite material part having a cellular structure that includes at least one cell delimited by walls. The method includes supplying at least a first core, providing a web of a first fibrous reinforcement comprising a plurality of long discontinuous fibers randomly distributed in a plane, and producing at least one strip of the first fibrous reinforcement. The method further includes producing a second fibrous reinforcement in the shape of a sock, inserting the first core into the sock, draping the strip around the sock containing the first core, placing the sock containing the first core and the wrapped strip in a mold, and thermocompression.

Abstract: Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

Abstract: An aircraft turbine engine with a main axis includes: an arm that is radial with respect to the main axis, extending through an air flow duct; a support wall belonging to the radial arm and which has two openings; a plurality of electric harnesses extending partially through the radial arm and for which a section of each harness is secured to the support wall of the arm; and two mounting blocks, in which each mounting block is associated with a group of sections of harness.

Abstract: Mobile robot for inspecting a turbomachine comprising at least a measuring device and a body including an assembly of at least three rigid segments each having two opposite longitudinal ends, the longitudinal ends of each segment being equipped with a hinge including a ball joint, each ball joint comprising a motorized wheel mounted therearound, the measuring device being mounted on a ball joint located at one end of the body.