METHOD FOR OPTIMISING THE SPECIFIC CONSUMPTION OF A TWIN HELICOPTER
Method for optimising the specific consumption of a helicopter equipped with two turboshaft engines ( 1, 2 ) which each comprise a gas generator ( 11, 21 ) provided with a combustion chamber (CC), each of these turboshaft engines ( 1, 2 ) being capable of operating on its own at a continuous flight speed, the other turboshaft engine ( 2, 1 ) therefore being at a speed referred to as super-idle at zero power, and, while the combustion chamber (CC) is ignited, this super-idle speed being assisted by the shaft (AE) of the gas generator being mechanically driven in rotation at this speed, so as to reduce the operating temperature and the fuel consumption of this gas generator.
1 . Method for optimising the specific consumption of a helicopter equipped with two turboshaft engines which each comprise a gas generator provided with a combustion chambers, each of these turboshaft engines being capable of operating on its own at a continuous flight speed, the other turboshaft engine therefore being capable of passing, at a speed referred to as super-idle at zero power, into a mode for accelerating the gas generator of this turboshaft engine by means of compatible driving together with a restart in an emergency output, characterised in that this super-idle speed is obtained while the combustion chamber of the gas generator is ignited, and in that this super-idle speed is assisted by the shaft of the gas generator being mechanically driven in rotation at this speed, so as to reduce the operating temperature and the fuel consumption of this gas generator.
2 . Optimisation method according to claim 1 , characterised in that the assistance is continued without interruption over the entire duration for which the engine is at super-idle speed.
3 . Optimisation method according to claim 1 , characterised in that the super-idle speed corresponds to approximately 10 to 40% of the rated speed of the gas generator at this speed.
4 . Optimisation method according to claim 1 , characterised in that the mechanical driving is provided by an electric motor, a mechanical drive device that is coupled to the other gas generator or to the rotor of the helicopter, or a mechanical drive device that operates using a power source such as a hydraulic or pneumatic source.