Improved Hybrid Turboprop Engine For Aircraft

Abstract: The invention relates to a hybrid turboprop engine (100) for an aircraft, comprising: a gas generator (12) which is supported by a generator shaft (14); a free turbine (11) which is supported by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), the turbine shaft (13) meshing with a main rotor (60) via a transmission system (50) comprising a first overrunning clutch (51) which is oriented such that the main rotor (60) cannot drive the free turbine (11); and a reversible electric machine (30) meshing with the main rotor via the transmission system (50) in order to drive the main rotor (60) during electric or hybrid operation, the turboprop engine comprising a single oil pump (40) meshing with the transmission system (50) in order to be driven selectively by the turbine shaft (13) or by the electric machine (30) according to the operating mode.

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