Abstract: An internal cooling system for an electric motor comprising a Drive End, DE, casing and a Non-Drive End, NDE casing, a stator with stator laminations and stator slots, head windings and stator slot winding turns, the internal cooling system comprising a first liquid cooling channel and a second liquid cooling channel, a periphery casing liquid cooling jacket connected to the first liquid cooling channel and to the second liquid cooling channel, DE and a NDE casing liquid cooling jackets configured to be established inside the DE and NDE casings, respectively, and connected to the first liquid cooling channel and to the second liquid cooling channel, respectively, and a slot-through liquid cooling jacket connected to the NDE and a DE casing liquid cooling jackets and configured to be established through the stator slots and in contact with the head windings and the stator slot winding turns to extract winding losses.

Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A propeller-type propulsion system for aircraft, comprises a propeller, a plurality of electric motors comprising nested coaxial respective driveshafts, and a gearbox having an output shaft onto which the propeller is mechanically coupled, and an input shaft to which the coaxial driveshafts of the electric motors are mechanically coupled. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.

Abstract: An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary DC electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. The contactors are linked in pairs to prevent them from being closed simultaneously. The second secondary network powers the generator-starter to start a fuel-burning engine. The first secondary network can be powered by the generator-starter to power electrical components. A secondary voltage of the second secondary electrical network is greater than the voltage of the first secondary electrical network, thus making it possible to optimize the weight of the electrical architecture. The two secondary electrical networks may also be powered from autonomous sources of electricity as a replacement for the primary network to power the generator-starter and the electrical components.

Abstract: A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.

Abstract: A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).

Abstract: A separately excited electric machine having a stator provided with at least one exciter unit and a rotor provided with strips. Each exciter unit comprises two secondary magnetic circuits and one primary magnetic circuit. Each secondary magnetic circuit comprises a stator exciter winding and two annular yokes provided with teeth. The primary magnetic circuit comprises a rotor exciter winding and an annular ring. First magnetic fluxes generated by the primary magnetic circuit circulate around loops in each strip and second magnetic fluxes generated by the secondary magnetic circuits circulate around loops in the strips, the teeth, and the ring. Each strip thus has a first north pole and a first south pole, with the teeth comprising in alternation second north poles and second south poles.

Abstract: An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary DC electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. The contactors are linked in pairs to prevent them from being closed simultaneously. The second secondary network powers the generator-starter to start a fuel-burning engine. The first secondary network can be powered by the generator-starter to power electrical components. A secondary voltage of the second secondary electrical network is greater than the voltage of the first secondary electrical network, thus making it possible to optimize the weight of the electrical architecture. The two secondary electrical networks may also be powered from autonomous sources of electricity as a replacement for the primary network to power the generator-starter and the electrical components.

Abstract: An electric machine includes a stator and a rotor, with the stator being equipped with at least one annular exciter unit that includes a coil and at least two annular yokes, with the rotor being equipped with a structure and at least one annular receiver unit. Each receiver unit includes at least two rows of magnets. Two sides of each yoke include teeth distributed angularly in a regular manner, and the teeth of the two adjacent yokes fit onto a face of the exciter unit, alternately forming north poles and south poles. Each row of the magnets is positioned opposite one face, forming an air gap with the exciter unit, with the electric machine thus including at least two air gaps, with a 3D magnetic flux thus circulating inside the said electric machine, dividing and regrouping itself in the vicinity of the magnets and of the yokes.

Abstract: An electric machine including a stator that is provided with at least one exciter unit including a coil, at least two annular yokes and at least one row of intermediate pieces, and a rotor having a structure and at least one receiver unit including at least two series of at least two rows of magnets. Two sides of each yoke include the first teeth, fitting with the intermediate pieces on a face of the exciter unit and alternatingly forming the second north poles and the second south poles. Each series is positioned opposite one face, forming an air gap with the exciter unit, with the electric machine thus including at least two air gaps, with a flux thus circulating inside the electric machine, dividing and regrouping itself in the vicinity of the magnets and of the yokes.

Abstract: A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).

Abstract: An aircraft (1) having at least one rotor (2) driven by a main gearbox (3), at least one fuel-burning engine (4), an on-board electricity network (7), and at least one electrical machine (10) corresponding to the engine (4) and capable of operating both in electric motor mode and also in electricity generator mode, each electrical machine (10) being mechanically connected to said main gearbox (3) by first connection means (20) and being electrically connected to said on-board electricity network (7). Second mechanical connection means (40) connect each electrical machine (10) mechanically to a gas generator (5) of an engine.

Abstract: A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).

Abstract: A separately excited electric machine having a stator provided with at least one exciter unit and a rotor provided with strips. Each exciter unit comprises two secondary magnetic circuits and one primary magnetic circuit. Each secondary magnetic circuit comprises a stator exciter winding and two annular yokes provided with teeth. The primary magnetic circuit comprises a rotor exciter winding and an annular ring. First magnetic fluxes generated by the primary magnetic circuit circulate around loops in each strip and second magnetic fluxes generated by the secondary magnetic circuits circulate around loops in the strips, the teeth, and the ring. Each strip thus has a first north pole and a first south pole, with the teeth comprising in alternation second north poles and second south poles.

Abstract: A method of assisting a pilot of a single-engined rotary wing aircraft (1) during a stage of flight in autorotation, said aircraft (1) including a hybrid power plant having an engine (13), an electric machine (12), and a main gearbox (11). Said aircraft (1) also includes electrical energy storage means (14) and a main rotor (2) mechanically connected to said hybrid power plant (5). According to said method, while in flight, the operation of said engine (13) is monitored in order to detect a failure thereof, in particular by monitoring for a drop of power on said main rotor (2), and then in the event of a failure of said engine (13) being detected, said electric machine (12) is controlled to deliver auxiliary power We to said main rotor (2), thereby enabling the pilot of said aircraft (1) to be assisted in maneuvering said aircraft (1) during said stage of flight in autorotation following said failure.

Abstract: A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).

Abstract: An aircraft (1) having at least one rotor (2) driven by a main gearbox (3), at least one fuel-burning engine (4), an on-board electricity network (7), and at least one electrical machine (10) corresponding to the engine (4) and capable of operating both in electric motor mode and also in electricity generator mode, each electrical machine (10) being mechanically connected to said main gearbox (3) by first connection means (20) and being electrically connected to said on-board electricity network (7). Second mechanical connection means (40) connect each electrical machine (10) mechanically to a gas generator (5) of an engine.

Abstract: The present invention relates to an electric machine (1) consisting of a stator (10) that is provided with at least one exciter unit (11) consisting of a coil (12), at least two annular yokes (13a,13b) and at least one row of intermediate pieces (15), and a rotor (20) having a structure (21) and at least one receiver unit (22) consisting of at least two series (25) of at least two rows (24) of magnets (23). Two sides (131,132) of each yoke (13) consist of the first teeth (14), fitting with the said intermediate pieces (15) on a face (121) of the said exciter unit (11) and alternatingly forming the second north poles and the second south poles. Each series (23) is positioned opposite one face (121), forming an air gap (30) with the said exciter unit (11), with the electric machine (1) thus including at least two air gaps (30), with a flux F thus circulating inside the said electric machine (1), dividing and regrouping itself in the vicinity of the said magnets (23) and of the said yokes (13).