Abstract: The rapid assistance device applies to a free turbine engine of an aircraft having at least a first free turbine engine provided with a gas generator and associated with an electrical machine capable of operating both as a starter and as a generator, the first engine being capable of being put into a standby mode or into an unwanted shut-down mode, the electrical machine being powered from on on-board electrical energy power supply network. The device further includes at least one electrical energy storage member adapted to be electrically connected to the electrical machine associated with the first engine in order to provide a burst of assistance to the gas generator of that engine. The electrical energy storage member constitutes a non-rechargeable “primary” energy storage member that can be used once only.

Abstract: A wound element made up of a plurality of superposed layers of turns wound on a core, including a sheet of a material that is thermally conductive at least in its plane, which sheet is interposed between two of the superposed layers of turns and has an end projecting from these layers and including at least one temperature probe for delivering temperature information about the wound element.

Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.

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 rapid assistance device applies to a free turbine engine of an aircraft having at least a first free turbine engine provided with a gas generator and associated with an electrical machine capable of operating both as a starter and as a generator, the first engine being capable of being put into a standby mode or into an unwanted shut-down mode, the electrical machine being powered from on on-board electrical energy power supply network. The device further includes at least one electrical energy storage member adapted to be electrically connected to the electrical machine associated with the first engine in order to provide a burst of assistance to the gas generator of that engine. The electrical energy storage member constitutes a non-rechargeable “primary” energy storage member that can be used once only.

Abstract: An emergency power supply device for aircraft, including at least one air intake duct configured to receive a relative airflow during a flight of the aircraft, a turbine arranged in the duct, to be driven by the relative airflow, and at least one device for generating power for the aircraft, the turbine being connected to the power-generating device to produce power for the aircraft at least under flight conditions thereof.

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising a synchronous starter-generator (ENG S/G) intended to be coupled to an aircraft engine, a rectifier (R) capable of transforming alternating voltage into direct voltage, an auxiliary synchronous starter-generator (AUX S/G) intended to be coupled to an auxiliary power group, a first, a second and a third power converter (CV1, CV2, CV3) capable of transforming direct voltage into alternating voltage or vice versa, and at least one battery (BATT).

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G1, S/G2) intended to be coupled to an engine (Engine1) of the aircraft, at least one conversion path comprising a plurality of power converters (CVn, CV?n) associated with switching means suitable for supplying at least one charge (CAC1, CAC2, CAC3, CAC4, P1, P2) from at least one source (S/G1, S/G2, AUX S/G1, AUX S/G2, GPU1, GPU2), and at least one distribution path suitable for supplying electrical charges (CT1n, SW1n, CT2n, SW2n).