Embodiments of the invention are shown in the figures, where a gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan about a rotational axis at a lower rotational speed than the core shaft, wherein the gearbox is an epicyclic gearbox with a plurality of planet gears arranged in first and second sets of planet gears, the planet gears of the first set being positioned displaced relative to the planet gears of the second set in a direction parallel to the rotational axis.

Embodiments of the invention are shown in the figures, where a gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan about a rotational axis at a lower rotational speed than the core shaft, wherein the gearbox is an epicyclic gearbox with a plurality of planet gears arranged in first and second sets of planet gears, the planet gears of the first set being positioned displaced relative to the planet gears of the second set in a direction parallel to the rotational axis.

A planetary gear mechanism includes a sun gear rotatable about an axis, a first shaft that is fixed to the sun gear and is rotatable integrally with the sun gear, a plurality of planetary gears that mesh with the sun gear and are rotatable about a center line thereof parallel to the axis, an internal gear that includes internal teeth facing inside in a radial direction to mesh with the planetary gears and is rotatable about the axis, a second shaft that extends in the axial direction to be connected to the internal gear and rotates about the axis together with the internal gear, and a reinforcing member that is fixed to an outer peripheral surface of the internal gear and is formed in an annular shape of a material having a higher specific strength than that of a material forming the internal gear.

A planetary gear mechanism includes a sun gear rotatable about an axis, a first shaft that is fixed to the sun gear and is rotatable integrally with the sun gear, a plurality of planetary gears that mesh with the sun gear and are rotatable about a center line thereof parallel to the axis, an internal gear that includes internal teeth facing inside in a radial direction to mesh with the planetary gears and is rotatable about the axis, a second shaft that extends in the axial direction to be connected to the internal gear and rotates about the axis together with the internal gear, and a reinforcing member that is fixed to an outer peripheral surface of the internal gear and is formed in an annular shape of a material having a higher specific strength than that of a material forming the internal gear.

A planetary gear transmission has a sun gear, a ring gear, at least one first planet gear, and at least one second planet gear. The first planet gear and the second planet gear are arranged on a planet carrier, and the sun gear, the ring gear, the first planet gear, and the second planet gear mesh with one another. The planetary gear transmission is characterized in that the planet carrier has a first planet carrier part and a second planet carrier part. The first planet carrier part and the second planet carrier part are designed such that the planet carrier parts are rotated relative to each other starting from a base position and can be fixed in their respective rotated position relative to each other, wherein the at least one first planet gear is connected to the first planet carrier part, and the at least one second planet gear is connected to the second planet carrier part.

A gearwheel for a gear system for a planetary gear system of a chassis assistance system. The gearwheel is divided into at least a first spur gear and a second spur gear which are spaced apart from one another along a common rotational axis. The gearwheel has, in addition, an open spring ring with a first end, which is supported in a circumferential direction against the first spur gear, and a second end, which is supported in the direction opposite to the circumferential direction against the second spur gear in such manner that by rotating the spur gears, relative to one another about the common rotational axis, the spring ring can be stressed in order to exert a restoring torque on the spur gears. A recess is formed on at least one of the spur gears for holding part of the spring ring.

A gearwheel for a gear system for a planetary gear system of a chassis assistance system. The gearwheel is divided into at least a first spur gear and a second spur gear which are spaced apart from one another along a common rotational axis. The gearwheel has, in addition, an open spring ring with a first end, which is supported in a circumferential direction against the first spur gear, and a second end, which is supported in the direction opposite to the circumferential direction against the second spur gear in such manner that by rotating the spur gears, relative to one another about the common rotational axis, the spring ring can be stressed in order to exert a restoring torque on the spur gears. A recess is formed on at least one of the spur gears for holding part of the spring ring.

An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×10.sup.9 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×10.sup.8 Nm/rad. A method of operation of such an engine is also disclosed.

A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element

A series of planetary gearboxes includes a plurality of subseries of planetary gearboxes. Each of the plurality of subseries includes a planetary gear carrier of a planetary stage, at least two rolling bearings, and a planetary gear mounted on the at least two rolling bearings. The at least two rolling bearings in a first one of the first plurality of subseries have a first bearing width and in a second one of the first plurality of subseries having a second bearing width.