Abstract: An annular combustion chamber for a turbine engine is provided. The chamber includes an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall. Each injector head includes at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head. Each injection system includes at least one swirler including air-passing channels of sections with axes that are inclined relative to the plurality axis of the swirler at an angle that is substantially equal to a helix angle of the helical channel, to within ±10°, and are oriented in a same direction as the channel about the longitudinal axis of the swirler.

Abstract: A bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.

Abstract: The invention relates to a turbomachine bearing support (1) supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising: a truncated part (11) having a diameter increasing from upstream to downstream; a flange part (12) which extends from the truncated part (11) as far as the bearing (5, 6) to which it is fixed by an axial flange (121), and having at its downstream end a radial internal flange (17) fixed to an oil inlet cover defining with the bearing (5, 6) an oil inlet container (170); oiled air clearance ducts (71) projecting downstream relative to the flange part (12) and on the oil inlet container (170) and to the other side upstream of the flange part (12) directly radially externally relative to the axial flange (121).

Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).

Abstract: A system paints the external and internal faces of a splayed end of a hollow shaft, with a rotary paint bench. This splayed end includes an end support face and an opposite support face. The system includes a fixing ring applied against the end support face and a counter-ring applied against the opposite support face as well as a fixing device, an end hub fixed to the fixing ring in line with the splayed end, and including a running belt suitable for resting on two rollers of the bench, a hollow external hub including two half-hubs delimiting a running belt suitable for resting on two rollers of the bench, and fixed to the counter-ring while surrounding the splayed end.

Abstract: A hub of an intermediate casing for an aircraft turbojet engine, including an inner shell intended to define a primary flow space of a primary gas stream into a turbojet engine, and at least one intermediate space, the inner shell being provided with at least one primary port and at least one movable door forming a primary air passage conduit, the door being capable of collecting, from the primary port, air flowing in the primary gas space and of sending the air collected in this way, via the intermediate space, towards a secondary air passage conduit. The primary conduit has an inner surface including, from upstream to downstream, a converging upstream part, then a nonconverging downstream part, in which the downstream part includes two portions of downstream side surface, and in which the upstream portion further includes two portions of upstream side surface.

Abstract: A piece of electronic equipment of a turbomachine, including a wall of which the inner surface defines at least one channel for the passage of a ventilating air stream of which the outlet opens on an outer surface of the wall with a view to discharging the ventilating air stream towards the outside of the equipment, wherein, at the outlet, a mechanism for diverting and/or guiding at least a portion of the discharged air stream, over at least a part of the outer surface of the wall.

Abstract: A device for controlling the pitch of the blades of a rotor is provided. The device includes a radial shaft, the rotation of which controls the pitch of the blades; a guiding bearing for guiding the radial shaft; a nut which tightens the guiding bearing along the radial axis; and a circumferential rib extending as a protrusion towards the outside of the nut, for guiding a lubrication oil towards the outside of the nut.

Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

Abstract: The disclosure relates to a tool for fitting an inner bearing race carrying a bearing cage and rollers and screws in a turbomachine, comprising two sectored cylindrical casings which respectively cover an upstream end part of the race and the bearing cage, a cylindrical annulus which surrounds the second casing, and a locking ring which is fitted on an upstream part of the first casing and which has means for axially pressing against the annulus and for axially clamping the second casing between the annulus and the heads of the screws carried by the flange.

Abstract: A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap.

Abstract: A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral faces and defined longitudinally between a leading edge and a trailing edge. On each of its lateral faces the pylon includes a series of deflectors that are transversely spaced apart from one another and that define between them convergent and curved channels configured to accelerate air streams flowing within the channels on aircraft takeoff or in flight to deflect the air streams towards a jet of the engine.

Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.

Abstract: An acoustic panel intended to be fixed internally to a fan casing of a turbojet engine, including an exterior face and an interior face which are curved about an axis, and two axially opposed transverse faces, the exterior curved face having at least one first recess on the side of a first transverse face and at least one second recess on the side of the opposite transverse face, said recesses each an attachment, in which said recesses do not open onto the interior curved face of the panel. Also covered are the turbojet engine including these panels and the method of mounting them.

Abstract: A device for guiding variable pitch diffuser vanes of a turbine engine is provided. The device includes a first ring having an axial portion at its periphery that is extended by a collar extending radially outwards; a second ring mounted around the axial portion of the first ring so as to cooperate therewith to define a plurality of outwardly open sockets; a plurality of cylindrical bushings, each mounted in a respective socket for the purpose of receiving a guide pivot of a diffuser vane; and a resilient clamping ring for cooperating with one of the rings in order to clamp the two rings axially one against the other.

Abstract: A system for attaching electrical equipment to a metallic support and including a pin designed to be inserted through a through-housing of the metallic support and a metallic insert of the electrical equipment, and a device for insulating the metallic support, extending between the metallic support and the metallic insert. The system also includes a mechanical retention device designed to apply load to the insulating device so as to keep them in contact with the metallic support and with the metallic insert.

Abstract: An engine includes systems for changing the pitch of propeller blades, a system for an upstream propeller including a linear actuator and a transmission mechanism connecting the actuator to the blades to transform the sliding of the actuator into a rotation of the blades, the upstream propeller including a rotatable housing rigidly connected to a rotatable shaft supported in a static housing of the turbine engine by an upstream bearing and by a downstream bearing. The rotatable housing of the upstream propeller includes a support rigidly connected to the rotatable housing and surrounding the static housing. The actuator is annular and fixed outside to the support, the transfer mechanism includes connecting rods and rotatable radial arms traversing the gaseous flow path, and the downstream bearing is radially located between the static housing and the support.

Abstract: A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

Abstract: An aircraft turbopropeller includes two coaxial contra-rotating unducted propellers, upstream and downstream respectively, each propeller including an annular row of blades. The blades of the downstream propeller have a reverse sweep in relation to that of the blades of the upstream propeller. The leading edges of the blades of the downstream propeller extend radially outwards from downstream to upstream, at least over a radially outer portion of the blades.