Abstract: A method for hard surface deposition on aluminum metal parts of a turbine engine using MIG welding equipment which includes a pulsed current generator and pulsed filler metal wire feed, wherein the deposition is achieved using a filler metal wire whose composition is of the same nature as the composition of the aluminum alloy of the part to undergo hard surface deposition, with the pulsed metal wire feed and speed of deposition on the metal part of the turbine engine being adapted to carry out deposition without hot fissuring.

Abstract: A field of vehicles propelled by reaction, and more specifically to a method of suppressing the pogo effect in such a vehicle. A feed system for feeding a reaction engine of the vehicle includes a hydraulic accumulator enabling a selection to be made from among a plurality of predetermined operating levels, each corresponding to a different volume of gas. In the method, if a first reference criterion is not satisfied by the current level, the hydraulic accumulator is ordered to make a transition, preferably to an alternative level selected from among alternative levels for which the first reference criterion is satisfied and for which no hydraulic resonant frequency crosses any current mechanical resonant frequency during the transition.

Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

Abstract: A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.

Abstract: A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

Abstract: A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.

Abstract: A machine for weaving or winding a fiber preform on a mandrel having an axis of rotation that is substantially horizontal and that serves to receive the preform, the machine having a plurality of cameras pointing towards the underside of the fiber preform in order to scan the hidden face of the fiber preform and acquire images of the hidden face; an image analysis module for processing these images of the hidden face of the fiber preform in a plurality of adjacent scan windows, and for extracting weaving patterns therefrom and comparing them with reference weaving patterns previously stored in the module; a motor for driving the mandrel in rotation about its axis of rotation; and a control unit for stopping rotation of the mandrel if the result of the comparison reveals a difference of appearance between the two weaving patterns.

Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

Abstract: A device for simulating an ingestion of chunks of ice by an engine, including: a main tank forming a cavity for a fuel, and connected to an inlet of the engine by a pipe; an injection system including an injection member arranged in the pipe; a secondary tank forming a cavity for a fuel, which tank is connected to the injection system by a selector member; and a reservoir connected firstly to a reserve of water and secondly to the injection system via the selector member. The selector member is configured to place the injection system selectively in communication with the secondary tank or with the reservoir to inject a determined quantity of water into the engine.

Abstract: A method of drilling a part, or a turbine engine part, by a pulse laser generator including a cavity in which there is mounted a solid bar for generating laser pulses, the method including determining values of a plurality of operating parameters of the laser generator for forming orifices of predetermined diameter in the part, and taking account, among the parameters, of a setpoint value for the temperature of the laser cavity, which value is determined as a function of characteristics of the orifices to be drilled.

Abstract: A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Abstract: A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds and being secured thereto. The part is made of composite material and is obtained by densifying a fiber preform with a matrix. The fiber preform includes a set of yarns extending continuously along a path passing longitudinally along the preform portions of at least two consecutive vanes by passing through the inner shroud preform portion and the outer shroud preform portion, and the woven fiber reinforcement yarns extends continuously in the circumferential direction along an inner shroud segment and along an outer shroud segment between which the consecutive vanes extend.

Abstract: A device for centring and guiding the rotation of a turbine engine shaft, in which the outer race of a bearing is retained axially upstream and downstream by a retaining mechanism cooperating with a bearing bracket and with a coupling mechanism including elastically deformable mechanism connecting the outer race to the bearing bracket, the retaining mechanism being separate from a protecting ring of the device. A method of assembling such a device is also described. The retaining mechanism is pre-assembled with the coupling mechanism prior to the final assembly of the coupling mechanism with the bearing bracket. The device and the method have the combined advantages of axially retaining the outer race in two opposing directions and having a particularly straightforward assembly.

Abstract: A device for supplying oil under pressure to a linear actuator of a turbine engine, in which the actuator includes an internal fixed portion and an external movable portion and a regulating device for regulating and supplying oil to chambers of the actuator, is provided. The regulating device is mounted radially outside the movable portion of the actuator, and the fixed portion of the actuator includes on its upstream end portion oil passage channels of which the outlets open radially outwards. The device further includes an oil distribution ring which is mounted on the upstream end portion of the fixed portion and which includes internal conduits of which the inlets communicate with the outlets of the channels of the fixed portion and the outlets open axially downstream and are connected to the regulating device.

Abstract: Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

Abstract: A method provides a device having a feeder vessel, a building vessel with a bottom and a fabrication plate that is movable in vertical translation, a transfer system suitable for depositing powder from the feeder vessel to the building vessel as a powder layer of constant thickness, and a high energy beam optical system suitable for scanning the surface of the deposited powder layer. A powder is placed in the feeder vessel. A first series of powder layers is deposited on the fabrication plate. The particles of powder are melted or sintered to form a plurality of columns of material that are separated from one another by particles of powder. A second series of layers of powder is deposited on the first series of layers of powder particles to form a single-piece element. A thermal insulation platform is formed between the fabrication plate and said single-piece element.

Abstract: An angular diffuser sector for a turbine engine compressor is provided. The sector includes an inner shroud; an outer shroud; a vane; a casing element mounted at least in part around one of the shrouds and having an open groove facing an axial end of the corresponding shroud; a wedge-forming fitting interposed between the casing element and the corresponding shroud, the wedge presenting a first surface that contacts with a bearing surface of the axial end of the corresponding shroud, and a second surface that is inclined relative to the first surface and that contacts with a corresponding sloping surface of the groove in the casing element; and a device that exerts an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its second surface in contact with the sloping surface of the groove in the casing element.

Abstract: A method of monitoring an actuator system including a control device, a torque motor having a voltage Umc across its terminals and actuating a servo-valve, and an actuator controlled by the servo-valve, is provided. The control device is suitable for delivering to the torque motor a control current Icmd as a function of a current setpoint I_c and of a measured current Imes. The monitoring method includes: comparing the voltage Umc measured across the terminals of the torque motor with a predetermined threshold voltage Vthresh; and if the voltage across the terminals of the torque motor is less than or equal to the predetermined threshold voltage, raising an alarm and indicating a failure of the servo-valve. The comparison of the voltage Umc is performed only if the control current Icmd is greater than a predetermined threshold current Iinhib, with a control current less than that inhibiting any signaling of a servo-valve failure.

Abstract: A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to the engine using connecting rods, or in a first bore provided in a front surface of the pylon; prepositioning the assembly including the engine and the front engine fastener relative to the pylon by placing the first shear pin opposite a receiving cavity, the receiving cavity being either the first bore, if the first shear pin has been positioned in the first opening, or the first opening, if the first shear pin has been positioned in the first bore; and inserting the first shear pin into the receiving cavity.

Abstract: A device for metal coating of fibers, for example ceramic fibers, by a liquid process, the device including a crucible containing a liquid metal bath through which a fiber is drawn to be coated with the metal, and a cooling system positioned downstream from the metal bath to solidify the metal sheath created around the fiber by capillarity. The cooling system includes at least one nozzle for ejecting a compressed gas towards the coated fiber, and the system is sized such as to solidify the metal on the periphery of the coated fiber over a length of no more than 200 mm.