METHOD FOR OPTIMIZING SPECIFIC CONSUMPTION OF FUEL OF TWO-MOTOR HELICOPTER

摘要

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.