The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

An aircraft turbomachine with a reduction gear has a first shaft and a second shaft having one same axis of rotation, the second shaft being rotationally driven by the first shaft via the reduction gear, the first shaft having elastically deformable means having bellows section(s) and being connected to the reduction gear by a connecting system likewise having elastically deformable means involving a hairpin or bellows section(s).

The present invention relates to a shaft for a propulsion system configured to rotate a reducing mechanism about a rotational axis, the shaft comprising: —a first end configured to engage with an input gear of the reducing mechanism, —a first bellows and a second bellows, the first bellows and the second bellows being rotationally symmetrical about the rotational axis, the first bellows extending between the first end and the second bellows, and —a frustoconical body mechanically connecting the first bellows and the second bellows.

An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

A coupling has: a first coupler rotatable about an axis and defining first connections distributed about the axis; a second coupler defining second connections distributed about the axis, the second connections offset from the first connections; and segments distributed about the axis and extending radially from the first connections to the second connections, a segment of the segments having a first end engaging a first connection of the first connections and a second end engaging a second connection of the second connections, the first end circumferentially offset from the second end, a face of the segment abutting against a face of the first coupler when the segment is inserted into the first connection in a first orientation such that a penetration depth of the segment into the first connection in the first orientation is less than the penetration depth in a second orientation opposite the first orientation.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

A shaft assembly for use with a turbine engine includes a shaft and a magnetic mode control unit. The shaft extends along an axis and is configured to rotate about the axis. The magnetic mode control unit is configured to control deflection of the shaft as the shaft rotates about the axis.

An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.

A device for assembling a turbine engine is configured for centering a shaft of a second module relative to a longitudinal axis of a hollow hub placed in front of a first module, the first module including a longitudinal cavity opening at the front into the hollow hub and passing through the first module until a rear end, the shaft configured to be inserted into the longitudinal cavity. The device includes a centering element and a guiding tube. The centering element is configured to be placed in the hollow hub. The guiding tube is configured to enter into at least one portion of the longitudinal cavity of the first module. The device is arranged so that the guiding tube slides inside the centering element. The invention also relates to the assembly formed by the device and a calibration jig, as well as an assembly method using same.

A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.