Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: 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.

Abstract: The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

Abstract: A gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to elements of the gear box, wherein the conduit system has at least one first supply line and one second supply line for supplying fluid to at least one element of the gear box. A leakage recovery facility is provided, by means of which at least a proportion of a leakage flow of fluid which originates from a first duct portion of the first supply line and which flows across at least one seal can be conducted to the second supply line.

Abstract: 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.

Abstract: A planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins an axially front carrier plate and an axially rear carrier plate, wherein the planet pins are connected to the carrier plates. Provision is made whereby the planet pins, at their axial ends, have in each case one platform, radially oriented slots are formed on the carrier plates, and the platforms are pushed via guide grooves into the radially oriented slots. The invention furthermore relates to a method for the assembly of a planetary gear box.

Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

Abstract: The invention relates to a planetary gearbox having a ring gear support, in particular in a geared fan engine, characterized by a bolt connection for connecting the ring gear support to a static component, wherein the bolt connections are arranged on the circumference of the ring gear support in the axial direction of the planetary gearbox, and the bolt connections are designed and arranged in such a way that there is a frictional joint with a defined frictional force between the ring gear support and the static component and that a material separation, in particular a gap, is arranged between the ring gear support and the static component.

Abstract: A planetary gearbox system with a ring gear, a sun gear, a carrier and planetary gears as parts in a geared aircraft turbofan engine, with one static part of the parts being in rest under nominal operation and with a kinematic switch device for decoupling the static part to become a rotatable part or with a kinematic switch device for coupling the rotatable part to become a static part. The invention also relates to a method for operating a planetary gearbox system.

Abstract: A mechanical clutch device for coupling two connecting parts in a gas turbo engine, in particular a geared aircraft turbofan engine, with means to automatically trigger a position change of one of the connecting parts relative to the respective other connecting parts and/or relative to an engine part from the first position into a second position in dependence of a torque effective on the connecting parts and/or the engine part, in particular through the transmission via a shaft, in particular a non-nominal torque, more in particular a reversal in the direction of the torque. It also relates to a method for operating a mechanical clutch device.

Abstract: A planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins an axially front carrier plate and an axially rear carrier plate, wherein the planet pins are connected to the carrier plates. Provision is made whereby the planet pins, at their axial ends, have in each case one platform, radially oriented slots are formed on the carrier plates, and the platforms are pushed via guide grooves into the radially oriented slots. The invention furthermore relates to a method for the assembly of a planetary gear box.

Abstract: The invention relates to a planetary gearbox having a ring gear support, in particular in a geared fan engine, characterized by a bolt connection for connecting the ring gear support to a static component, wherein the bolt connections are arranged on the circumference of the ring gear support in the axial direction of the planetary gearbox, and the bolt connections are designed and arranged in such a way that there is a frictional joint with a defined frictional force between the ring gear support and the static component and that a material separation, in particular a gap, is arranged between the ring gear support and the static component.

Abstract: A mechanical fuse device with two connecting parts coupled to a ring gear mount of a gearbox in a geared aircraft turbofan engine, with means to automatically trigger a position change of at least one of two the connecting parts relative to the respective other connecting part from a first position into a second position in dependence of a torque effective on at least one of the two connecting parts. It also relates to a method for operating a mechanical fuse device.

Abstract: A mechanical clutch device for coupling two connecting parts in a gas turbo engine, in particular a geared aircraft turbofan engine, with means to automatically trigger a position change of one of the connecting parts relative to the respective other connecting parts and/or relative to an engine part from the first position into a second position in dependence of a torque effective on the connecting parts and/or the engine part, in particular through the transmission via a shaft, in particular a non-nominal torque, more in particular a reversal in the direction of the torque. It also relates to a method for operating a mechanical clutch device.

Abstract: A planetary gearbox system with a ring gear, a sun gear, a carrier and planetary gears as parts in a geared aircraft turbofan engine, with one static part of the parts being in rest under nominal operation and with a kinematic switch device for decoupling the static part to become a rotatable part or with a kinematic switch device for coupling the rotatable part to become a static part. The invention also relates to a method for operating a planetary gearbox system.