| 摘要 |
A turbine engine for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator is disclosed. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration.
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