Abstract: A device for lubricating and cooling a turbomachine rolling bearing is at least partially annular. The device comprises a first duct and a second duct inclined with respect to the first duct. The first duct is configured to be in thermal contact with an outer ring of the rolling bearing that at least partially surrounds same. The second duct is fluidically connected to the first duct. The first duct is configured to circulate the lubricant for cooling the outer ring, towards a discharge outlet of the lubricant. The second duct is configured to eject the lubricant through a lubrication outlet towards the rolling bearing.

Abstract: A power transmission mechanism for a turbomachine is provided, having a reduction gear having a first gear and a second gear having different reduction ratios and each having a first gear wheel mounted so as to be able to rotate freely on a shared first axle and a second gear wheel mounted on a shared second axle; and a coupling member having an annular body with an axis of revolution having first and second rows of helical coupling teeth, which are respectively oriented opposite and substantially parallel to the first and second directions, the coupling member being mounted so as to rotate with and slide axially on said first axle so as to occupy at least two predetermined axial meshing positions in which the coupling teeth mesh with complementary meshing projections of one of the first gear wheels which is then made to rotate with the first axle.

Abstract: A contactless seal intended for being fitted in a wall and a shaft passing through an opening of the wall, the seal comprising a rotary member intended for being supported by the shaft and a stationary member intended for being supported by the opening, the stationary member being inserted around the rotary member while being rotatably movable relative to same, the rotary member having an outer surface provided with at least one circumferential rib and the stationary member having an inner surface provided with at least one groove, or vice-versa. Each rib is partially inserted into a corresponding groove in order to form a labyrinthine leak path. The rotary member and the stationary member are each made up of a single part, and the rotary member and/or the stationary member are obtained by additive manufacturing.

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: An air-flow circuit for air flow through a bearing enclosure of a turbine engine, the air-flow circuit including a supply system arranged such as to supply the air into the bearing enclosure; a discharge system arranged such as to discharge at least some of the air from the bearing enclosure; an oil-removal system connected to the discharge system, the oil-removal system being capable of reducing the amount of lubricant contained in the air coming from the discharge system; and a compressor arranged between the discharge system and the oil-removal system, the compressor being capable of increasing the air pressure at the intake of the oil-removal system.

Abstract: A device for lubricating and cooling a turbomachine rolling bearing is at least partially annular. The device comprises a first duct and a second duct inclined with respect to the first duct. The first duct is configured to be in thermal contact with an outer ring of the rolling bearing that at least partially surrounds same. The second duct is fluidically connected to the first duct. The first duct is configured to circulate the lubricant for cooling the outer ring, towards a discharge outlet of the lubricant. The second duct is configured to eject the lubricant through a lubrication outlet towards the rolling bearing.

Abstract: The reduction gear includes a pair of gears installed in parallel between two shafts and each provided with a mobile wheel free to move axially to engage in turn with one of the shafts and to transmit movement with different ratios. Since the gear teeth are helical, opposite forces on the reduction gear make it changeover from one reduction ratio to the other. No external control is necessary. Application to mechanical transmissions between an engine and a reversible electrical machine (starter or generator), that starts the motor with a large speed reduction and generates electricity with a smaller reduction.

Abstract: An oil jet for a turbine engine, comprising a body including a circulation pipe intended for the flow of a pressurized fluid. The jet's body comprises a first part and a second part between which a resiliently deformable membrane is inserted, said membrane being capable of deforming between a sealed position in which it prevents the circulation of the fluid in the pipe and a position in which it allows the circulation of fluid in the pipe. The second part includes bearing means configured to exert a force on the membrane positioned in the opposite direction to the circulation of fluid so as to preload the membrane when in blocked position.

Abstract: A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.

Abstract: A device for filtering a flow of gas conveying liquid or solid particles in a flow channel. According to the invention, the particles are imparted a speed that is high enough to project same by inertia into the opening of a recovery channel formed inside the flow channel, while the gas from the flow bypasses said opening due to a specific configuration of the flow conditions of a perfect fluid in the flow channel and in the collection channel.

Abstract: A contactless seal intended for being fitted in a wall and a shaft passing through an opening of the wall, the seal comprising a rotary member intended for being supported by the shaft and a stationary member intended for being supported by the opening, the stationary member being inserted around the rotary member while being rotatably movable relative to same, the rotary member having an outer surface provided with at least one circumferential rib and the stationary member having an inner surface provided with at least one groove, or vice-versa. Each rib is partially inserted into a corresponding groove in order to form a labyrinthine leak path. The rotary member and the stationary member are each made up of a single part, and the rotary member and/or the stationary member are obtained by additive manufacturing.

Abstract: To overcome defects in the supply of pressurized lubricant, a hydrodynamic bearing for guiding a shaft (14) includes a stationary outer annular wall, a rotatable inner annular wall (20), and a space (22) between the walls. The outer annular wall comprises an opening for supplying pressurized lubricant to the space so as to form a film of load-bearing fluid. The bearing includes a cavity (30) externally defined by the inner annular wall (20) and axially defined by two transverse annular walls (31A, 31B) secured to the shaft (14) and arranged on both sides of the cavity. The inner annular wall (20) comprises fluid connection orifices (32) connecting the cavity (30) to the space (22). The cavity (30) is divided into compartments (50, 52) by a partition wall (48) configured such that the cavity forms a lubricant supply for a transient operational phase.

Abstract: A power transmission mechanism for a turbomachine is provided, having a reduction gear having a first gear and a second gear having different reduction ratios and each having a first gear wheel mounted so as to be able to rotate freely on a shared first axle and a second gear wheel mounted on a shared second axle; and a coupling member having an annular body with an axis of revolution having first and second rows of helical coupling teeth, which are respectively oriented opposite and substantially parallel to the first and second directions, the coupling member being mounted so as to rotate with and slide axially on said first axle so as to occupy at least two predetermined axial meshing positions in which the coupling teeth mesh with complementary meshing projections of one of the first gear wheels which is then made to rotate with the first axle.

Abstract: An oil jet for a turbine engine, comprising a body including a circulation pipe intended for the flow of a pressurized fluid. The jet's body comprises a first part and a second part between which a resiliently deformable membrane is inserted, said membrane being capable of deforming between a sealed position in which it prevents the circulation of the fluid in the pipe and a position in which it allows the circulation of fluid in the pipe. The second part includes bearing means configured to exert a force on the membrane positioned in the opposite direction to the circulation of fluid so as to preload the membrane when in blocked position.

Abstract: The reduction gear includes a pair of gears installed in parallel between two shafts and each provided with a mobile wheel free to move axially to engage in turn with one of the shafts and to transmit movement with different ratios. Since the gear teeth are helical, opposite forces on the reduction gear make it changeover from one reduction ratio to the other. No external control is necessary. Application to mechanical transmissions between an engine and a reversible electrical machine (starter or generator), that starts the motor with a large speed reduction and generates electricity with a smaller reduction.

Abstract: A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.

Abstract: To overcome defects in the supply of pressurized lubricant, a hydrodynamic bearing for guiding a shaft (14) includes a stationary outer annular wall, a rotatable inner annular wall (20), and a space (22) between the walls. The outer annular wall comprises an opening for supplying pressurized lubricant to the space so as to form a film of load-bearing fluid. The bearing includes a cavity (30) externally defined by the inner annular wall (20) and axially defined by two transverse annular walls (31A, 31B) secured to the shaft (14) and arranged on both sides of the cavity. The inner annular wall (20) comprises fluid connection orifices (32) connecting the cavity (30) to the space (22). The cavity (30) is divided into compartments (50, 52) by a partition wall (48) configured such that the cavity forms a lubricant supply for a transient operational phase.

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: An air-flow circuit for air flow through a bearing enclosure of a turbine engine, the air-flow circuit including a supply system arranged such as to supply the air into the bearing enclosure; a discharge system arranged such as to discharge at least some of the air from the bearing enclosure; an oil-removal system connected to the discharge system, the oil-removal system being capable of reducing the amount of lubricant contained in the air coming from the discharge system; and a compressor arranged between the discharge system and the oil-removal system, the compressor being capable of increasing the air pressure at the intake of the oil-removal system.

Abstract: A device for filtering a flow of gas conveying liquid or solid particles in a flow channel. According to the invention, the particles are imparted a speed that is high enough to project same by inertia into the opening of a recovery channel formed inside the flow channel, while the gas from the flow bypasses said opening due to a specific configuration of the flow conditions of a perfect fluid in the flow channel and in the collection channel.