Abstract: The invention relates to a method and to a device for optimized global management of a power network of an aircraft comprising a plurality of items of power equipment, characterized in that it comprises a module 40 for selecting at least one optimization objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimization objective (19).

Abstract: The invention relates to a method and to a device for optimised global management of a power network of an aircraft comprising a plurality of items of power equipment, characterised in that it comprises a module 40 for selecting at least one optimisation objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimisation objective (19).

Abstract: A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector.

Abstract: A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector.