An electric propulsion system for a gas turbine engine may comprise an electric motor disposed within a nacelle of the gas turbine engine, wherein the electric motor is configured to receive a bypass air from a fan bypass duct for cooling the electric motor and the electric motor is configured to drive a low speed shaft of the gas turbine engine.

An electric propulsion system for a gas turbine engine may comprise an electric motor disposed within a nacelle of the gas turbine engine, wherein the electric motor is configured to receive a bypass air from a fan bypass duct for cooling the electric motor and the electric motor is configured to drive a low speed shaft of the gas turbine engine.

A method and system for managing power to an engine controller operatively coupled to an engine of an aircraft are described. The method comprises powering the engine controller from an aircraft battery, starting a timer in response to a predetermined trigger to maintain the engine controller powered by the aircraft battery for a predetermined time, and removing power from the aircraft battery to the engine controller when the timer expires.

A method and system for managing power to an engine controller operatively coupled to an engine of an aircraft are described. The method comprises powering the engine controller from an aircraft battery, starting a timer in response to a predetermined trigger to maintain the engine controller powered by the aircraft battery for a predetermined time, and removing power from the aircraft battery to the engine controller when the timer expires.

A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

A turning apparatus includes: an electric motor; a pinion gear that rotationally drives a wheel gear provided in a rotor in a first rotation direction and moves to a first position where the pinion gear can transmit a rotation of the electric motor to the wheel gear and a second position where the pinion gear cannot transmit the rotation of the electric motor to the wheel gear; a current value detection unit that detects a current value of the electric motor in a state where the pinion gear is positioned at the first position; and a control device that controls the electric motor to rotate the pinion gear in a second rotation direction opposite to the first rotation direction based on the current value detected by the current value detection unit.

A turning apparatus includes: an electric motor; a pinion gear that rotationally drives a wheel gear provided in a rotor in a first rotation direction and moves to a first position where the pinion gear can transmit a rotation of the electric motor to the wheel gear and a second position where the pinion gear cannot transmit the rotation of the electric motor to the wheel gear; a current value detection unit that detects a current value of the electric motor in a state where the pinion gear is positioned at the first position; and a control device that controls the electric motor to rotate the pinion gear in a second rotation direction opposite to the first rotation direction based on the current value detected by the current value detection unit.

Turbomachinery comprising first and second sets of rotors configured to operate on a working fluid. The machinery further comprises first and second sets of electric machines coupled to the respective first and second rotors, and a coupling arrangement arranged to couple adjacent rotors of the first and second rotor sets to provide for fixed ratio, contra-rotation of the first and second rotor sets.

A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.