Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, with at least one torque transmission device positioned in the drive train, the torque transmission device having an asymmetric torque transmission characteristic, so that torque is transmittable by the torque transmission device under a nominal rotational direction and no torque is transmittable by the torque transmission device in a non-nominal rotational direction.

Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, is provided. The gas turbine includes at least one form locking connection device in a drive train enabling a controlled disengagement of at least one engine part from the drive train in case of a mechanical failure of the gas turbine engine or a part thereof and wherein the at least one form locking connection device is positioned in a torque carrying shaft or a torque carrying part of a shaft and/or wherein the at least one form locking connection device is positioned between the torque bearing coupling of the gearbox with the fan shaft and a torque carrier of the gearbox and at least one load stop for bearing an essential axial load.

Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive shaft assembly driven by a turbine is provided. A driving side of the gearbox being driveably connected with at least one propulsive fan, with at least one mechanical fuse in the drive shaft assembly enabling a controlled disengagement of at least one engine part from the drive shaft assembly in case of a mechanical failure of the gas turbine engine or a part thereof and at least one load stop for bearing a load, in particular an axial or radial load in case of the mechanical failure of the gas turbine or a part thereof. A first mechanical fuse is positioned in a torque carrying shaft or a torque carrying part of a shaft, in particular in a torque bearing coupling between the shaft and the gearbox.

Abstract: The invention relates to a gas turbine engine, in particular an aircraft engine, comprising: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.

Abstract: A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox.

Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, with at least one torque transmission device positioned in the drive train, the torque transmission device having an asymmetric torque transmission characteristic, so that torque is transmittable by the torque transmission device under a nominal rotational direction and no torque is transmittable by the torque transmission device in a non-nominal rotational direction.

Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive shaft assembly driven by a turbine is provided. A driving side of the gearbox being driveably connected with at least one propulsive fan, with at least one mechanical fuse in the drive shaft assembly enabling a controlled disengagement of at least one engine part from the drive shaft assembly in case of a mechanical failure of the gas turbine engine or a part thereof and at least one load stop for bearing a load, in particular an axial or radial load in case of the mechanical failure of the gas turbine or a part thereof. A first mechanical fuse is positioned in a torque carrying shaft or a torque carrying part of a shaft, in particular in a torque bearing coupling between the shaft and the gearbox.

Abstract: A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox.

Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, is provided. The gas turbine includes at least one form locking connection device in a drive train enabling a controlled disengagement of at least one engine part from the drive train in case of a mechanical failure of the gas turbine engine or a part thereof and wherein the at least one form locking connection device is positioned in a torque carrying shaft or a torque carrying part of a shaft and/or wherein the at least one form locking connection device is positioned between the torque bearing coupling of the gearbox with the fan shaft and a torque carrier of the gearbox and at least one load stop for bearing an essential axial load.