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AssigneeSafran Helicopter Engines
InventorsBenjamin Nicolas Fulleringer, Antoine Pascal Moutaux, Romain Jean Gilbert Thiriet
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A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.
A transmission device for a hybrid aircraft, the aircraft comprising a turbomachine including at least one gas generator, a free turbine rotationally driven by a stream of gas generated by the gas generator, and a main rotor, the transmission device comprising a first reversible electric machine able to be coupled to a shaft of the free turbine by way of a first deactivatable coupling means, and to the main rotor, and a second reversible electric machine able to be coupled to a shaft of the gas generator by way of a second deactivatable coupling means, and to be coupled to the main rotor by way of a third deactivatable coupling means, the second deactivatable coupling means being configured to be activated when the second electric machine rotates in a first direction of rotation, and the third deactivatable coupling means being configured to be activated when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.
Dependencies are inferred from the claim text.