Abstract: A method of manufacturing a mechanical component made of steel including a surface-hardening phase. The method includes creating a rough form of the component with regions to be hardened, then successive case hardening with cooling without quenching, heating to an austenitizing temperature of the steel by induction heating the zones, and quenching.

Abstract: A circuit, an installation that uses the circuit, and its design method, the circuit for distributing electricity that can supply at least two loads from two sources, and including: conductors, some of which form outputs configured to be connected to external equipment, and switching devices configured to establish a path between each load and the two sources by connecting the loads and sources to the outputs. For at least one pair of determined loads, the two switching devices on the paths connecting each source to the two loads of the pair are integrated in a double-flow switch. The double-flow switch is connected at its central point to the output that can be connected to the corresponding source.

Abstract: A power transmission system for a turbine engine is provided. The power transmission system includes a transmission shaft that is connected to a drive shaft by bevel gears, and that drives equipment or accessories. The transmission shaft is designed to operate under supercritical conditions and includes a damper system for damping vibration at its resonant speed.

Abstract: A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Abstract: A gas turbine AGB has a front lateral face, a rear lateral face opposite from the front lateral face, and a peripheral rim closing the box. At least one gear train is mounted in the AGB and is made up of a plurality of gearwheels meshing together, and designed to be coupled to a drive shaft for driving an accessory. The AGB further comprises, mounted between a central shaft carrying each gearwheel and the drive shaft, a decoupling unit for decoupling the accessory and constituted by a dog clutch having axial teeth co-operating with complementary teeth of the central shaft. The dog clutch includes internal fluting engaged with the corresponding external fluting of the drive shaft. The decoupling unit is controlled by an electric actuator acting on the movement of a plunger pin having one end co-operating with an outer helical groove in the dog clutch.

Abstract: The invention relates to an accessory gearbox assembly for an aircraft turbine engine including: —a radial drive shaft (41); —an input gearbox (20) including an input gear, attachable onto a drive shaft (12) connecting a turbine (11) to a compressor (10) of the turbine engine, and an output gear secured to the radial drive shaft (41); —an accessory (51) including a stator, attachable to a housing (2) of the turbine engine, and a rotor that is rotatably mounted relative to the stator; and —a transfer gearbox (41) including an input gear, rotatably secured to the radial drive shaft (41), and an output gear rotatably secured to the rotor of the accessory (51). The input gear (45) engages with the output gear (46) so that, when the drive shaft (12) is rotated, the drive shaft rotates the rotor of the accessory (51) via the input gearbox (20), the radial drive shaft (41), and the transfer gearbox (41).

Abstract: An accessory gearbox for a turbomachine, the gearbox being equipped with a pump and including intermeshing pinions, one of which is formed as a single piece with a coaxial shank for driving a rotary part of the pump, wherein said rotary part is directly mounted on the shank.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including a device forming a fluid circulation passage configured to generate a pressure drop, created by stacking at least two elements. Each element includes a passage for carrying fluid configured to generate a pressure drop and including an inlet and an outlet. The outlet, or inlet, of the passage of one of the elements is, respectively, connected to the inlet, or to the outlet, of the passage of the other element.

Abstract: The invention concerns a planet carrier (5) for an epicyclic speed reduction gear, comprising an annular cage (7) comprising two sides (9, 10) extending radially, linked by bridges (16), seats (6) extending axially between the sides (9, 10) and being intended to support planet gears mounted rotating about the seats (6). One (9) of the sides (9, 10) of the cage (7) is immovably fixed to a torque output member (8), in such a way as to form a single structural assembly.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces.

Abstract: A circuit, an installation that uses the circuit, and its design method, the circuit for distributing electricity that can supply at least two loads from two sources, and including: conductors, some of which form outputs configured to be connected to external equipment, and switching devices configured to establish a path between each load and the two sources by connecting the loads and sources to the outputs. For at least one pair of determined loads, the two switching devices on the paths connecting each source to the two loads of the pair are integrated in a double-flow switch. The double-flow switch is connected at its central point to the output that can be connected to the corresponding source.

Abstract: An accessory relay for a turbine engine, including a housing in which at least one gear wheel is installed for mechanically driving an accessory mounted on the housing, the gear of the wheel being driven via an input shaft supplying torque required for the mechanical drive, the shaft of the wheel being supported by at least two ball or roller bearings, and passing through at least one of the walls of the housing via an opening positioned opposite the accessory and closed by a first accessory cover attached onto the housing, wherein, for at least one of the gear wheels, the shaft thereof passes through two walls of the housing via openings closed by covers attached onto the housing, and the outer races of the two bearings are supported by the covers.

Abstract: An aircraft drive chain including a plurality of main gears engaging with each other, a first main gear including a wall defining an inner space, an outer set of gear teeth being placed on an outer surface of the wall, the outer set of gear teeth engaging with at least one second main gear, a gear system being built into the inner space, the first main gear and the gear system being jointly configured so as to form a gearbox or reducer and ensure mechanical power transfer between a drive member and a slave member, the gear system being mounted onto the wall with a decoupling member.

Abstract: An aircraft drive chain including a plurality of main pinions meshing with each other, a first main pinion including a wall delimiting an inner volume, external teeth being provided on an outer surface of the wall, the external teeth meshing with at least one second main pinion, a gear system being incorporated in the inner volume, the first main pinion and the gear system being jointly configured to form a multiplier or reducer and to ensure a mechanical energy transfer between a driving member and a slave member.

Abstract: This gearbox to be assembled to a turbomachine portion and driven by a power take-off radial shaft thereof, includes several branches, the essential advantage of which is to allow a great amount of pieces of equipment to be driven to be accommodated, without implying a significant overall size in any dimension, since the gearbox remains close to the turbomachine and the pieces of equipment can be distributed on a large surface area. The housing (5) is divided into portions (27, 28) assembled to each other at the bends, in order to reduce its manufacturing cost.

Abstract: Mechanical test device including: an internal gear with internal teeth, configured to engage a pinion to be tested, the axis of the gear being fixed relative to the axis of the pinion to be tested; an internal gear support on which the gear is installed, a central movement transmission element configured to have a rotation movement about an axis fixed relative to the axis of the provided; a pinion to drive the gear, configured to engage the teeth of the gear; a mobile support on which the gear drive pinion is fixed; a support for the pinion to be tested, fixed relative to the support; and-an apparatus for putting the mobile support in rotation about the axis of the gear while the assembly composed of the pinion to be tested the gear the central transmission element and the pinion driving the gear is put into movement.

Abstract: An electronic device with cooling of a heat dissipation source, by a liquid metals spreader, the device including at least one heat dissipation source, at least one spreader through which at least one liquid metal circulation channel passes forming a loop routed below a heat dissipation source, at least one heat sink, and at least one electromagnetic pump moving the liquid metal in the at least one channel such that the liquid metal absorbs heat dissipated by a heat dissipation source and transports the absorbed heat to be evacuated by the heat sink. Each spreader includes at least two plates made of an electrical insulating material located on each side of at least one bar made of deformable material.

Abstract: This gearbox to be assembled to a turbomachine portion and driven by a power take-off radial shaft thereof, includes several branches, the essential advantage of which is to allow a great amount of pieces of equipment to be driven to be accommodated, without implying a significant overall size in any dimension, since the gearbox remains close to the turbomachine and the pieces of equipment can be distributed on a large surface area. The housing (5) is divided into portions (27, 28) assembled to each other at the bends, in order to reduce its manufacturing cost.

Abstract: An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces.

Abstract: An emergency power supply device for aircraft, including at least one air intake duct configured to receive a relative airflow during a flight of the aircraft, a turbine arranged in the duct, to be driven by the relative airflow, and at least one device for generating power for the aircraft, the turbine being connected to the power-generating device to produce power for the aircraft at least under flight conditions thereof.