An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

A dual-wound machine comprises a dual-wound generator supplying power to two separate powered zones. The generator comprises a wound rotor with a field winding and a stator with two sets of phase windings and a field control loop that controls the excitation voltage applied to the field winding and therefore the magnetic field produced by the rotor, in order to maintain a constant field flux in the generator and mitigate dynamic coupling between the two sets of phase windings when supplying power to unbalanced loads.

An assembly according to an embodiment of the present disclosure includes, among other things, a synchronous machine including a rotating portion and a stationary portion, the rotating portion including at least one rotating diode coupled to a field winding, and the stationary portion including a stator winding and an exciter winding. A control unit includes a first gate and a second gate. The exciter winding is connected in series to the first gate and the second gate during a first operating mode to energize the exciter winding. The exciter winding is electrically connected in series to a first gate but is electrically disconnected from the second gate in a second, different operating mode to electrically disconnect the exciter winding from an exciter energy source. A method of operating a synchronous machine is also disclosed.

A high voltage power generating system includes a first poly-phase permanent magnet generator including at least one control winding and a plurality of power windings, a second poly-phase permanent magnet generator including at least one control winding and a plurality of power windings, the first and second poly-phase permanent magnet generators being arranged in series in at least one operational mode, and the first poly-phase permanent magnet generator being phase shifted relative to the second poly-phase permanent magnet generator such that residual voltage output of the first poly-phase permanent magnet generator is offset by the second poly-phase permanent magnet generator during a first operational mode.

Systems for parallel excitation for a synchronous machine are provided. Aspects include a rectification circuit coupled to an output of a permanent magnet generator, and an excitation winding connected to an output of the rectification circuit, a direct current (DC) power source connected between an output of the rectification circuit and the excitation winding, wherein the excitation winding supplies an excitation voltage to an excitation armature in a main generator during a during a plurality of operational modes, wherein the plurality of operational modes comprise a startup mode and a generator mode, wherein a DC excitation voltage is provided to the excitation windings by the DC power source during the startup mode, and wherein the DC excitation voltage is provided to the excitation windings by the rectification circuit during the generator mode.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

A synchronous machine and related systems include a stator and rotor separated by an air gap. The rotor includes a rotating DC power supply coupled to exciter windings disposed adjacent the air gap. Power from air gap harmonics, including air gap slot harmonics induce current in the exciter windings, which is rectified and supplied to the rotor field windings. In operation, a desired current level in the rotor field windings can be achieved through control of the DC power supply or superposition of harmonics into the stator winding current which induces the prescribed current in exciter windings.

The present disclosure relates to motor vehicles. The teachings thereof may be embodied in the operation and control of an externally excited electrical generator in an on-board electrical system of a motor vehicle. An example method may include: setting the excitation voltage within the scope of regulating an actual output voltage of the generator at a predetermined setpoint output voltage of the generator; evaluating load requirements of at least one peak load consumer supplied from the on-board electrical system; identifying exceptional situations based on the load requirements; and in the event of an exceptional situation, setting an associated temporary excitation output voltage of the generator.

A rotary transformer for an electrical machine includes a rotary printed circuit board and a stator printed circuit board. The rotary printed circuit board is operatively connected to the stator printed circuit board for relative rotation with respect to the stator printed circuit board. A conductor is fixed to the one of the printed circuit boards and includes a spiral coil for transferring electrical energy between the rotary printed circuit board and stator printed circuit board.

A voltage regulator, an operation method thereof, and a voltage regulating system, and a mobile vehicle are provided. The voltage regulator coupled to an alternator and a battery includes a voltage detection unit which is coupled to the alternator and a startup assisting unit. The voltage detection unit operatively generates an enable signal responsive to an output voltage of the alternator. The startup assisting unit is coupled to the alternator, the battery, and the voltage detection unit. The startup assisting unit operatively generates a first exciting current to excite a rotor coil according to the enable signal. When the voltage detection unit detects that the output voltage is greater than a predetermined voltage threshold, the voltage detection unit outputs the enable signal causing the startup assisting unit to generate the first exciting current to the rotor coil, thereby facilitating the alternator to establish voltage under low rotational speed.