A gas turbine engine system includes, in serial flow communication, an engine compressor configured to compress air, a combustor in which the compressed air is mixed with fuel and ignited to generate a stream of combustion gases, and a turbine configured to extract energy from the combustion gases. An electric generator is configured to be driven by the turbine and generate electric energy during use. An electric motor is configured to be driven by electric energy generated by the electric generator. The electric motor is configured in use to drive the engine compressor.

A turning device for a turbomachine comprises a plurality of electromagnets connectable to an electric power source; a rotor magnetically coupled with the electromagnets, connectable to a main shaft of the turbomachine and having a rotation axis, the electromagnets are arranged facing the rotor in order to induce eddy currents on a surface of the rotor and apply a torque to the rotor, thus rotating the main shaft.

A turning device for a turbomachine comprises a plurality of electromagnets connectable to an electric power source; a rotor magnetically coupled with the electromagnets, connectable to a main shaft of the turbomachine and having a rotation axis, the electromagnets are arranged facing the rotor in order to induce eddy currents on a surface of the rotor and apply a torque to the rotor, thus rotating the main shaft.

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.

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 bowed rotor prevention system for a gas turbine engine includes a bowed rotor prevention motor. A motor shaft of the bowed rotor prevention motor is operable to drive rotation of the gas turbine engine through an engine accessory gearbox. The motor shaft interfaces with an air turbine operable to rotate an output shaft mechanically linked to the engine accessory gearbox. The bowed rotor prevention system also includes a controller operable to engage the bowed rotor prevention motor and drive rotation of the gas turbine engine below an engine starting speed until a bowed rotor prevention threshold condition is met.

A bowed rotor prevention system for a gas turbine engine includes a bowed rotor prevention motor. A motor shaft of the bowed rotor prevention motor is operable to drive rotation of the gas turbine engine through an engine accessory gearbox. The motor shaft interfaces with an air turbine operable to rotate an output shaft mechanically linked to the engine accessory gearbox. The bowed rotor prevention system also includes a controller operable to engage the bowed rotor prevention motor and drive rotation of the gas turbine engine below an engine starting speed until a bowed rotor prevention threshold condition is met.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

A bowed-rotor prevention system for a turbomachine is disclosed. The system comprises a first turbomachine having a first shaft rotatably supported by a plurality of bearings, a second turbomachine having a second shaft rotatably coupled to the first rotatable shaft, and a pump having a third shaft rotatably coupled to the second shaft. The system further includes a gear box having a fourth shaft rotatably coupled to the third shaft by an clutch configured to operate in a freewheel condition when the first shaft is rotating faster than a first predetermined speed, and further configured to rotatably engage the fourth shaft to the third shaft when the first shaft is rotating slower than a second predetermined speed to thereby drive a rotation of the third shaft, wherein the first predetermined speed is faster than the second predetermined speed.