The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

An aircraft (100) with a rotary wing (40) is equipped with a propulsion system (10). The aircraft (100) includes a rotating mast (50) that rotates the rotor wing (40). The propulsion system (10) includes a pole (20) mechanically connected to the rotating mast (50) of the aircraft (100), where at least one end of the pole (20) is equipped with a motor (30) configured to rotate the pole (20) around the axis of the rotating mast (50) in such a way that the rotation of the pole (20) can be used to rotate the rotating wing (40). At each end of the pole (20) is placed a motor group (30), where each motor group (30) includes a pair of counter-rotating propellers (32,32), said pair of counter-rotating propellers (32,32′) being arranged in such a way as to generate a rotational torque to rotate the pole (20).

An aircraft (100) with a rotary wing (40) is equipped with a propulsion system (10). The aircraft (100) includes a rotating mast (50) that rotates the rotor wing (40). The propulsion system (10) includes a pole (20) mechanically connected to the rotating mast (50) of the aircraft (100), where at least one end of the pole (20) is equipped with a motor (30) configured to rotate the pole (20) around the axis of the rotating mast (50) in such a way that the rotation of the pole (20) can be used to rotate the rotating wing (40). At each end of the pole (20) is placed a motor group (30), where each motor group (30) includes a pair of counter-rotating propellers (32,32), said pair of counter-rotating propellers (32,32′) being arranged in such a way as to generate a rotational torque to rotate the pole (20).

A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.

A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.

An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a rate of rotation of from 3 to 8 times that of the outer fan.

An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a tip speed of from 1 to 3 times that of the outer fan.

The invention relates to an aircraft thruster (30) comprising at least a first propeller (32) provided with a plurality of radial blades (34) extending about an axis (A) of rotation of the said first propeller (32), which is driven in rotation by a first electric motor (36), the electrical supply means of which comprise power circuits (42) carried by a fairing of the thruster characterised in that the power circuits (42) are arranged in an annular manner in an annular part (40) integral with the fairing of the thruster (30), this annular part (40) being arranged around the said first propeller (32).

A coaxial contra-rotating circumferential thruster includes: an input end, a one-way commutator, a two-way deflector, a steering support and two output ends. The input end is connected to a power device. The one-way commutator converts one rotation into two rotations having the same rotation speed and opposite rotation directions. The two-way deflector respectively indirectly connects two shafts of a contra-rotating sleeve shaft to two output shafts thereof by means of two bevel gear pair. Two unidirectional deflecting torques respectively generated by the two bevel gear pairs have the same magnitude and opposite directions. By transferring by means of a bracket or an output sleeve shaft, the two unidirectional deflecting torques cancel each other. The two output ends are respectively connected to two propellers (or rotors). A turnaround control device controls the steering support to be turned around, the control torque required for co-rotating and contra-rotating is the same.

A coaxial contra-rotating circumferential thruster includes: an input end, a one-way commutator, a two-way deflector, a steering support and two output ends. The input end is connected to a power device. The one-way commutator converts one rotation into two rotations having the same rotation speed and opposite rotation directions. The two-way deflector respectively indirectly connects two shafts of a contra-rotating sleeve shaft to two output shafts thereof by means of two bevel gear pair. Two unidirectional deflecting torques respectively generated by the two bevel gear pairs have the same magnitude and opposite directions. By transferring by means of a bracket or an output sleeve shaft, the two unidirectional deflecting torques cancel each other. The two output ends are respectively connected to two propellers (or rotors). A turnaround control device controls the steering support to be turned around, the control torque required for co-rotating and contra-rotating is the same.