A turbomachine for hybrid aircraft, including a gas generator carried by a generator shaft, at least one free turbine carried by a turbine shaft and driven in rotation by a gas stream generated by the gas generator, a main rotor, and at least one reversible electric machine, the turbine shaft being a through shaft and extending axially between a first end engaged with the electric machine, and a second end engaged with the main rotor.

A propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

A propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

Disclosed is a turbogenerator, in particular for an electrically-driven rotary wing aircraft, comprising a gas generator equipped with a first shaft, at least one reversible electrical machine, and a free turbine provided with a second shaft and caused to rotate by a gas flow generated by the gas generator. The second shaft is coupled to the at least one electrical machine during all phases of operation of the turbomachine, and the turbomachine further comprises a single mechanical coupling means for coupling the first mechanical shaft to the second mechanical shaft when the electrical machine is operating in motor mode and mechanically uncoupling the first mechanical shaft from the second mechanical shaft when the electrical machine is operating in generator mode.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.