Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter includes a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurised air from the turboshaft engine; a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Abstract: The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.

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: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterised in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.

Abstract: The invention relates to a device for assisting a propulsion system of a single-engine helicopter, comprising an engine connected to a power transmission gearbox (15) suitable for rotating a rotor (88) of the helicopter, characterised in that it comprises: a turbine (18) for driving in rotation an output shaft (34) that is mechanically connected to said power transmission gearbox (15); and controlled means (16) for supplying said drive turbine (18) with pressurised fluid in order to allow said turbine (18) to transform the power from said pressurised fluid into mechanical power for rotating said output shaft (34).

Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterised in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.

Abstract: Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurised liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurised liquid.

Abstract: The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step (10) of receiving data (27, 28, 29) that are representative of the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change of mode would be most relevant; a step (12) of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step (14) of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.

Abstract: 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.

Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.

Abstract: An emergency starter that allows responsiveness within a few seconds, without having disadvantages associated with mass and size of a back-up hydraulic or pneumatic starter. An instantaneous gas thrust of pyrotechnic type is coupled with a positive displacement transmission generator in conjunction with automatic coupling to/uncoupling from a set that is to be started. An emergency start-up system includes at least one pyrotechnic gas generator connected to an electrical initiator itself connected to a computer, a positive displacement motor housing straight-cut gears, the pyrotechnic gas generator being coupled to the motor by an inlet in the casing. The motor includes a mechanism of connection capable of moving at one end of the drive shaft configured to couple the transmission shaft to a driven shaft of the set that is to be started via a centrifugal clutch.

Abstract: A method and architecture to reduce specific fuel consumption of a twin-engine helicopter without compromising safety conditions regarding minimum amount of power to be supplied, to provide reliable in-flight restarts. The architecture includes two turbine engines each including a gas generator and with a free turbine. Each gas generator includes an active drive mechanism keeping the gas generator rotating with a combustion chamber inactive, and an emergency assistance device including a near-instantaneous firing mechanism and mechanical mechanism for accelerating the gas generator. A control system controls the drive mechanism and emergency assistance devices for the gas generators according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory of the system.