Patent ID: 8201414
Filing Date: 2012-06-19
Classification: F01D,F02C,F05D

Abstract:
1. A turbine engine of an aircraft, comprising: a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator; a first electricity generator coupled to a shaft of the free turbine; a storage unit electrically connected to the first electricity generator; and an electric motor/generator electrically connected to the storage unit and mechanically coupled to a shaft of the gas generator, wherein the shaft of the free turbine is coupled to a rotor of a helicopter, wherein the storage unit supplies power to the motor/generator during a stage of turbine engine acceleration to provide a quantity of additional rotational kinetic energy to the gas generator shaft and stores a quantity of kinetic energy drawn from the gas generator shaft by the motor/generator in a form of electrical energy during a stage of turbine engine deceleration, and wherein the storage unit is recharged by the first electricity generator.