Abstract: The invention relates to a device (1) for separating an air/oil mixture comprising an air/oil mixture inlet (8), an oil receiving chamber (9), an air circulation duct (11), at least one filter element (21) rotatably coupled to a rotating drive shaft (12), the device (1) being designed so that the mixture from the above-mentioned inlet (8) opens into the chamber (9) and is driven through the rotatably driven filter element (21), so that the oil contained in the mixture is centrifuged radially outside the filter element (21) and fed into the oil receiving chamber (9), the filtered air opening into the air flow line (11), characterized in that the rotating drive shaft (12) is coupled to a turbine (26) capable of being driven in rotation by at least part of the filtered air flow, the turbine (26) comprising an outlet (29) of the filtered flow which opens to the outside.

Abstract: The invention relates to an assembly comprising a drive gearbox (10) for an aircraft (1) and an accessory (30), the gearbox comprising: a connecting shaft (110) adapted to be driven by the propulsion system, a main shaft (120) adapted to be driven by the connecting shaft (110), and two bevel gears (122, 123) which are integral with the main shaft (120) and have different diameters (d122, d123), the accessory comprising: a high-speed accessory shaft (31) comprising a bevel gear (310), a low-speed accessory shaft (32) comprising a bevel gear (320), such that each gear (310, 320) on the accessory shafts (31, 32) meshes with one of the two bevel gears (122, 123) on the main shaft (120), so that the two accessory shafts (31, 32) rotate at different speeds relative to one another.

Abstract: The invention relates to a device (1) for separating an air/oil mixture comprising an air/oil mixture inlet (8), an oil receiving chamber (9), an air circulation duct (11), at least one filter element (21) rotatably coupled to a rotating drive shaft (12), the device (1) being designed so that the mixture from the above-mentioned inlet (8) opens into the chamber (9) and is driven through the rotatably driven filter element (21), so that the oil contained in the mixture is centrifuged radially outside the filter element (21) and fed into the oil receiving chamber (9), the filtered air opening into the air flow line (11), characterized in that the rotating drive shaft (12) is coupled to a turbine (26) capable of being driven in rotation by at least part of the filtered air flow, the turbine (26) comprising an outlet (29) of the filtered flow which opens to the outside.

Abstract: Speed reduction gear comprising two intermediate transmission lines, in particular for a turbine engine, comprising an input line (12) and an output line that is driven by the input line via said intermediate transmission lines, said intermediate transmission lines being substantially parallel, characterized in that said reduction gear comprises means for distributing loads between said intermediate lines, said load distribution means comprising swiveling coupling means (30) for rotatably coupling one end of the input line, and oil-damping means (40, 50) for damping radial movements of an opposite end of the input line.

Abstract: A gearbox to be attached to a turbine engine to drive at least one apparatus annexed to the turbine engine, the gearbox including a housing; a power take-off member capable of engaging with a radial shaft of the turbine engine; at least one kinematic chain located inside the housing and capable of transmitting the rotational movement of the power take-off member to at least one rotatable shaft of an apparatus. The kinematic chain includes a first end and a second end. The power take-off member is linked to the kinematic chain by a gear having convergent axes and located between the first end and the second end of the kinematic chain.

Abstract: Speed reduction gear comprising two intermediate transmission lines, in particular for a turbine engine, comprising an input line (12) and an output line that is driven by the input line via said intermediate transmission lines, said intermediate transmission lines being substantially parallel, characterised in that said reduction gear comprises means for distributing loads between said intermediate lines, said load distribution means comprising swiveling coupling means (30) for rotatably coupling one end of the input line, and oil-damping means (40, 50) for damping radial movements of an opposite end of the input line.

Abstract: The invention relates to an assembly comprising a drive gearbox (10) for an aircraft (1) and an accessory (30), the gearbox comprising: a connecting shaft (110) adapted to be driven by the propulsion system, a main shaft (120) adapted to be driven by the connecting shaft (110), and two bevel gears (122, 123) which are integral with the main shaft (120) and have different diameters (d122, d123), the accessory comprising: a high-speed accessory shaft (31) comprising a bevel gear (310), a low-speed accessory shaft (32) comprising a bevel gear (320), such that each gear (310, 320) on the accessory shafts (31, 32) meshes with one of the two bevel gears (122, 123) on the main shaft (120), so that the two accessory shafts (31, 32) rotate at different speeds relative to one another.

Abstract: A gearbox to be attached to a turbine engine to drive at least one apparatus annexed to the turbine engine, the gearbox including a housing; a power take-off member capable of engaging with a radial shaft of the turbine engine; at least one kinematic chain located inside the housing and capable of transmitting the rotational movement of the power take-off member to at least one rotatable shaft of an apparatus. The kinematic chain includes a first end and a second end. The power take-off member is linked to the kinematic chain by a gear having convergent axes and located between the first end and the second end of the kinematic chain.

Abstract: A starter/generator mechanically coupled to a gas turbine transmission housing is disclosed. The starter/generator includes a generator with a rotor forming a field winding and a stator forming an armature, and an energizer with a stator forming a field winding and a rotor forming an armature connected to the generator field winding. The generator rotor and the energizer rotor are mounted on a common shaft with a transmission housing gear wheel, on either side of the gear wheel.

Abstract: An assembly includes a gearbox for a gas turbine having a geartrain, and at least one starter/generator coupled mechanically to the gearbox. The starter/generator includes a generator module with a first casing, a generator housed in the first casing, and a first shaft constrained to rotate with the rotor of the generator, projecting from the first casing, and carrying a first mechanical coupling member; an exciter module, including a second casing, an exciter housed in the second casing, and a second shaft distinct from the first shaft, constrained to rotate with the rotor of the exciter, projecting from the second casing, and carrying a second mechanical coupling member; and an electrical connection including a rectifier and at least one connector for connecting the secondary circuit of the exciter to the primary circuit of the generator.

Abstract: A gas-turbine starter/generator comprises: a generator module comprising a first casing, a generator housed in the first casing, and a first shaft constrained to rotate with the rotor of the generator, projecting from the first casing, and carrying a first mechanical coupling member; an exciter module, comprising a second casing, an exciter housed in the second casing, and a second shaft distinct from the first shaft, constrained to rotate with the rotor of the exciter, projecting from the second casing, and carrying a second mechanical coupling member; and an electrical connection comprising a rectifier and at least one connector for connecting the secondary circuit of the exciter to the primary circuit of the generator. The mechanical coupling members are coupled to a common gearwheel or to respective different gearwheels of a gearbox of the gas turbine.

Abstract: A high-performance plain bearing provided with a friction coating including a bronze layer whereof the pores are filled with a PTFE-type fluoroplastic paste filled with molybdenum bisulphide. The production method includes sintering a layer of bronze powder on the metal support of the bearing, a vacuum ionic cleaning, applying a filled fluoroplastic film, passing the component through a die and after sintering the paste, a final pass in the die for final dimensioning. During sintering and passing through the die an anti-adhesive and wear-resistant coating, based on titanium nitride or the like, is applied on the equipment.

Abstract: A turbojet engine having a fan (12) driven by a speed-reducing gear unit (23) whose input is driven by a turbine shaft (22). The speed-reducing gear unit (23) includes a planet gear (24) affixed to a turbine shaft (22), a ring gear (28) joined to a fan shaft (12) and a plurality of satellite gears (25) mounted on a stationary satellite support (27) and having helical teeth which operatively engage with helical teeth of the ring gear and the planet gear to balance axial loads along the turbine shaft and the fan shaft.

Abstract: A turbojet engine having a fan (12) driven by a speed-reducing gear unit (23) whose input is driven by a turbine shaft (22). The speed-reducing gear unit (23) includes a planet gear (24) affixed to a turbine shaft (22), a ring gear (28) joined to a fan shaft (12) and a plurality of satellite gears (25) mounted on a stationary satellite support (27) and having helical teeth which operatively engage with helical teeth of the ring gear and the planet gear to balance axial loads along the turbine shaft and the fan shaft.