An air starter for starting a turbine engine that includes a housing, a turbine, an output shaft, and at least one bearing. The housing can define an interior where the turbine couples to the output shaft. A primary air flow path extends through the housing where air from the turbine can be exhausted through a primary outlet or a cooling outlet.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.

A starter assembly includes a housing defining an interior, a rotatable pinion gear wherein the rotatable pinion gear extends exteriorly of the housing and operably coupling to a combustion engine, a torque sensor providing a torque output indicative of a torque experienced by the pinion gear, and a controller module configured operate a starting sequence for the starter assembly.

A starter assembly includes a housing defining an interior, a rotatable pinion gear wherein the rotatable pinion gear extends exteriorly of the housing and operably coupling to a combustion engine, a torque sensor providing a torque output indicative of a torque experienced by the pinion gear, and a controller module configured operate a starting sequence for the starter assembly.

A drive assembly for a gas turbine engine according to an exemplary embodiment includes, among other things, an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, and at least one engagement feature on a component of the gear train. An actuator is engageable with the at least one engagement feature to cause the accessory drive shaft to rotate. A method of driving a section of a gas turbine engine is also disclosed.

A drive assembly for a gas turbine engine according to an exemplary embodiment includes, among other things, an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, and at least one engagement feature on a component of the gear train. An actuator is engageable with the at least one engagement feature to cause the accessory drive shaft to rotate. A method of driving a section of a gas turbine engine is also disclosed.