Abstract: A pressurized air supply unit (1; 1?) for an aircraft, comprising: a load compressor (30; 30?) configured to supply pressurized air (3), the load compressor (30; 30?) having a compressor shaft (23; 23?); and a drive portion (10) configured to supply power via an output shaft (20); the pressurized air supply unit (1; 1) being characterized in that it comprises: a gearbox (50); an electric motor (40), the electric motor (40) being coupled to said compressor shaft (23; 23?) via the gearbox (50); and a coupling system (25) configured to enable the output shaft (20) to drive the compressor shaft (23; 23?) and to prevent the compressor shaft (23; 23?) from driving the output shaft (20), and in that the output shaft (20) and the compressor shaft (23) lie on the same axis.

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Abstract: A pressurized air supply unit (1; 1?) for an aircraft, comprising: a load compressor (30; 30?) configured to supply pressurized air (3), the load compressor (30; 30?) having a compressor shaft (23; 23?); and a drive portion (10) configured to supply power via an output shaft (20); the pressurized air supply unit (1; 1) being characterized in that it comprises: a gearbox (50); an electric motor (40), the electric motor (40) being coupled to said compressor shaft (23; 23?) via the gearbox (50); and a coupling system (25) configured to enable the output shaft (20) to drive the compressor shaft (23; 23?) and to prevent the compressor shaft (23; 23?) from driving the output shaft (20), and in that the output shaft (20) and the compressor shaft (23) lie on the same axis.

Abstract: A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.

Abstract: The invention relates to a device for starting a gas turbine, comprising an initiation system able, on command, to rotate said gas turbine. The starting device comprises means for receiving information representing the rotation speed of the gas turbine, means for calculating a set torque value according to said information representing the rotation speed of the gas turbine, and means for transmitting said set torque value to the initiation system, and the means for calculating the set torque value are suitable for making a comparison of the information representing the rotation speed of the gas turbine with a predetermined speed profile and calculating the set torque value from said comparison.

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: Method for supplying non-propulsive power for an aircraft, comprising the driving of a shaft (13) of an environmental control system (1) of the aircraft by a combination of energy sources selected from: an auxiliary power unit (4), a starter/generator (18), and auxiliary-air supply means (63).

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Abstract: A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.