Abstract: An installation for mounting an outer sun gear in a reduction gear. The reduction gear includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The installation includes a frame for supporting the reduction gear along its longitudinal axis, and first and second torque applicators, such as cylinders, that apply a torque around an axis of first and second rings, respectively. The first ring is configured to engage with the first crown of the outer sun gear and the second ring is configured to engage with a second crown of the outer sun gear.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.

Abstract: A ring gear (114) for an epicyclic or planetary reduction gear (110) of a turbomachine, in particular of an aircraft, said ring gear extending about an axis and comprising first and second coaxial annular elements (114a, 114b) and comprising, respectively, two inner annular toothing sets (150) of different orientation, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges (114ab, 114bb) for attaching said first and second elements to each other, characterised in that one of said first and second flanges comprises, at its outer periphery, a cylindrical centring rim (164) configured to cooperate with the outer periphery of the other of said first and second flanges.

Abstract: An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.

Abstract: A ring gear for an epicyclic or planetary reduction gear of a turbomachine, in particular of an aircraft, said ring gear extending about an axis X and comprising first and second coaxial annular elements and comprising, respectively, two inner annular toothing sets of different orientation, each of said toothing sets having a pitch diameter and a median plane substantially perpendicular to said axis and with an intersection point designated Y in an axial cross-section of the ring gear, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges for attaching said first and second elements to each other, wherein each of said first and second flanges comprises a peripheral portion extending in a plane that is angled with respect to said axis X and that passes substantially through said intersection point Y.

Abstract: A planet carrier for an epicyclic speed reduction gear, comprising a torque transmission member of longitudinal axis A and an annular cage extending around the axis A and connected to a longitudinal end of the member, said cage comprising two flanks extending essentially radially with respect to the axis A and connected by bridges, seats extending axially between the flanks and being intended for supporting planet gears mounted rotatably about the seats, characterized in that said bridges comprise bars which cross one another essentially in the shape of an X, and of which the ends located on the side of said member are connected to said member by a ring extending around said axis A and comprising a continuous internal annular channel.

Abstract: A method of mounting a gearbox is described. The gearbox includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The method consists in applying simultaneously and independently a first torque to the first crown centered on the axis of the first crown and a second torque is applied to the second crown centered on the axis of the second crown, the first torque and the second torque having identical values.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.

Abstract: An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.

Abstract: Device of the reduction gear or differential type for a turbine engine of an aircraft. A central sun gear and a row of planet gears, each of the planet gears are rotationally guided by at least one bearing extending around a tubular support. The tubular support includes an inner cavity for the reception of oil and through-orifices for the passage of oil of the tubular support to the at least one bearing. A member for circulating the oil is mounted in the cavity and includes at least one oil duct intended to be connected to an oil supply. The oil is intended to flow from the at least one duct into the inner cavity to form an oil film in contact with said tubular support, and to flow through the orifices.

Abstract: A planet carrier for an epicyclic speed reduction gear, comprising a torque transmission member of longitudinal axis A and an annular cage extending around the axis A and connected to a longitudinal end of the member, said cage comprising two flanks extending essentially radially with respect to the axis A and connected by bridges, seats extending axially between the flanks and being intended for supporting planet gears mounted rotatably about the seats, characterized in that said bridges comprise bars which cross one another essentially in the shape of an X, and of which the ends located on the side of said member are connected to said member by a ring extending around said axis A and comprising a continuous internal annular channel.

Abstract: The invention relates to a method for manufacturing a component able to rotate about an axis, comprising a step of incorporating a magnetic material into the powder during the manufacture of the rotating component, in at least one predefined zone of the component formed. The invention also relates to a rotating component obtained using this method and to a system for measuring rotation of the rotating component obtained by this method, by using at least one sensor able to detect the passage of the zone into which the magnetic material is incorporated.

Abstract: A ring gear (114) for an epicyclic or planetary reduction gear (110) of a turbomachine, in particular of an aircraft, said ring gear extending about an axis and comprising first and second coaxial annular elements (114a, 114b) and comprising, respectively, two inner annular toothing sets (150) of different orientation, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges (114ab, 114bb) for attaching said first and second elements to each other, characterised in that one of said first and second flanges comprises, at its outer periphery, a cylindrical centring rim (164) configured to cooperate with the outer periphery of the other of said first and second flanges.

Abstract: A ring gear for an epicyclic or planetary reduction gear of a turbomachine, in particular of an aircraft, said ring gear extending about an axis X and comprising first and second coaxial annular elements and comprising, respectively, two inner annular toothing sets of different orientation, each of said toothing sets having a pitch diameter and a median plane substantially perpendicular to said axis and with an intersection point designated Y in an axial cross-section of the ring gear, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges for attaching said first and second elements to each other, wherein each of said first and second flanges comprises a peripheral portion extending in a plane that is angled with respect to said axis X and that passes substantially through said intersection point Y.

Abstract: Device of the reduction gear or differential type for a turbine engine of an aircraft. A central sun gear and a row of planet gears, each of the planet gears are rotationally guided by at least one bearing extending around a tubular support. The tubular support includes an inner cavity for the reception of oil and through-orifices for the passage of oil of the tubular support to the at least one bearing. A member for circulating the oil is mounted in the cavity and includes at least one oil duct intended to be connected to an oil supply. The oil is intended to flow from the at least one duct into the inner cavity to form an oil film in contact with said tubular support, and to flow through the orifices.