The present disclosure provides a turbine engine, comprising a core turbine engine comprising a turbine and a compressor adapted to be driven by the turbine via a rotor; as accessory gearbox connected with the rotor; and a flexible shaft having a first end connected with the accessory gearbox and a second end extending toward outside for being coupled to an external power source.

A gas turbine engine comprises a gearbox including a first epicyclic gearbox and a second epicyclic gearbox. The first epicyclic gearbox comprises a first sun gear meshing with the first planet gears and the first planet gears meshing with a first annulus gear. The second epicyclic gearbox comprises a second sun gear meshing with the second planet gears and the second planet gears meshing with a second annulus gear. An input shaft is arranged to drive the first sun gear and a first planet gear carrier is arranged to drive a propulsor. The first and second annulus gears are fixed to a static structure. A first clutch is arranged between the first planet gear carrier and the second planet gear carrier and a second clutch is arranged between the second sun gear and the input shaft. The gearbox is more efficient at cruise conditions.

Disclosed is a rotating component for a turbine engine including a first rotating component having a first snap surface and a second rotating component having a second snap surface wherein the first snap surface is configured to interlock with the second snap surface, and further wherein at least one of the first snap surface and the second snap surface have a friction enhancing material.

A power-on/off command is output to a breaker for switching when a frequency difference between a plurality of electric power supply sources is within a predetermined range and a phase difference between the plurality of electric power supply sources is within a predetermined range, in switching of electric power supply between the plurality of electric power supply sources. A generator drive rotation speed of a transmission device is feedback controlled so that the frequency difference is maintained at a value within the predetermined range and the phase difference is maintained at a value within the predetermined range when the detected frequency difference is within the predetermined range and the detected phase difference is within the predetermined range. A generator rotation speed command is calculated by adding to the rotation speed command of the transmission device an output value obtained by subjecting the detected phase difference to a proportional-integral-control.

A disk assembly may include: a first disk engaged with a compressor section of a gas turbine; a second disk engaged with a turbine section of the gas turbine; and a third disk disposed between the first and second disks, and transferring torque applied to the second disk to the first disk. The third disk has a plurality of legs formed on an inner circumferential surface thereof, the plurality of legs being in contact with an outer circumferential surface of a tie bolt of the gas turbine.

A method of operating a gas turbine engine. The method includes determining a first compressor non-dimensional rotational speed set point, determining a current first compressor rotational speed and first compressor inlet temperature, and transferring power between the first and second shafts such that the first shaft non-dimensional rotational speed matches the set point.

A starting device for driving a compressor-side rotary shaft of a two-shaft type gas turbine engine at a time of starting the gas turbine engine includes: a starter motor serving as a drive source for the compressor-side rotary shaft; a speed increaser configured to increase a speed of rotation of the starter motor; and a clutch mechanism configured to disconnectably connect the starter motor and the compressor-side rotary shaft with each other, the clutch mechanism being provided between the compressor-side rotary shaft and the speed increaser.

Disclosed is a two-piece shaft assembly for a driven turbocharger with a traction drive. The turbo shaft is attached to a turbine and compressor, and is inserted into a traction barrel that has traction surfaces to mate to the traction drive. In this way, the traction drive can be assembled with only the traction barrel, and the turbo shaft can be inserted through the barrel at the end to simplify assembly.

A device drives a shaft of a jet engine for inspection purposes. The device has: a drive having a part co-rotating with the shaft. The co-rotating part of the unit is configured to lie against a spinner of the shaft and is secured in a non-rotatable manner to at least one fan blade arranged on the shaft using at least one strap.

Provided is a toroidal continuously variable transmission that can create a jet of oil resistant to the influence of wind generated by rotation of a power roller, thereby feeding a sufficient amount of oil to the power roller to cool the power roller with the oil; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes a discharge structure including an outlet that discharges an oil. The discharge structure includes first and second oil passages connected with each other inside the discharge structure, and arranged such that the oil flowing through the first oil passage and the second oil passage collide with each other in the vicinity of the outlet and that a jet of oil discharged from the outlet forms a flattened shape extending along a rotational direction of the power roller.