Electric generator

1. An electric generator assembly for an aircraft comprising:

a main generator comprising a main rotor and a main stator, the main stator comprising a first three-phase winding and a second three-phase winding, the first and second three-phase windings are arranged in parallel, have separate neutral points, and are 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 of equal to or approximately equal to 30 degrees,

the main generator further comprises a first main generator rectifier configured to convert a three-phase AC voltage from the first three-phase winding into a DC voltage and a second main generator rectifier configured to convert a three-phase AC voltage from the second three-phase winding into a DC voltage, the first and second main generator rectifiers each having a first terminal and a second terminal,

the main generator also comprises a single main generator interphase transformer having a first branch electrically coupled with the first terminal of the first main generator rectifier and a second branch electrically coupled with the first terminal of the second main generator rectifier, the second terminal of the first main generator rectifier and the second terminal of the second main generator rectifier are not electrically coupled with an interphase transformer, and

wherein the first and second three-phase windings are paralleled through the single main generator interphase transformer.

2. The electric generator assembly of claim 1 , wherein the first and second three-phase windings are configured to operate with full 120 degree conduction in each phase.

3. The electric generator assembly of claim 1 , wherein the first bridge and the second bridge of the single main generator interphase transformer are electrically coupled with a first DC voltage output, and wherein the second terminal of the first main generator rectifier and the second terminal of the second main generator rectifier are directly electrically coupled with a second DC voltage output without an interphase transformer being positioned therebetween.

4. The electric generator assembly of claim 1 , further comprising:

an exciter comprising an exciter rotor and an exciter stator, wherein the exciter rotor applies an exciter voltage to the main rotor of the main generator through a rotating rectifier.

5. The electric generator assembly of claim 4 , wherein the exciter voltage is a DC exciter voltage, and wherein the exciter further comprises an exciter rectifier for converting a three-phase AC exciter voltage to the DC exciter voltage.

6. The electric generator assembly of claim 4 , further comprising:

a permanent magnet generator (PMG) comprising a PMG rotor and a PMG stator, wherein the PMG stator provides a PMG voltage to the exciter stator.

7. The electric generator assembly of claim 6 , further comprising:

a current modulator for reducing a PMG current provided to the exciter stator.

8. The electric generator assembly of claim 7 , wherein the electric generator assembly includes a power output control, wherein the power output control is operably coupled to the current modulator.

9. The electric generator assembly of claim 1 , wherein the main generator comprises a DC power output, and wherein the electric generator assembly includes a power output control configured to affect an amount of voltage induced in the first and second three-phase windings, wherein the power output control comprises a DC current sensor operable with the DC power output.

10. The electric generator assembly of claim 1 , wherein the main generator comprises a positive DC power output and a negative DC power output, and wherein the main generator further comprises a voltage clamp electrically coupled between the positive and negative DC power outputs, wherein the voltage clamp is configured as an active clamp having a transistor arranged in series with a resistor.

11. The electric generator assembly of claim 1 , wherein the main generator provides a high power DC power output.

12. An aircraft electrical system comprising:

a combustion engine; and

an electric generator assembly comprising a main generator comprising a main rotor and a main stator, the main generator rotor driven directly or indirectly by the combustion engine, the main stator comprising a first three-phase winding and a second three-phase winding, the first and second three-phase windings are arranged in parallel, have separate neutral points, and are 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 of equal to or approximately equal to 30 degrees,

the main generator further comprises a first main generator rectifier configured to convert a three-phase AC voltage from the first three-phase winding into a DC voltage and a second main generator rectifier configured to convert a three-phase AC voltage from the second three-phase winding into a DC voltage, the first and second main generator rectifiers each having a first terminal and a second terminal,

the main generator also comprises a single main generator interphase transformer having a first branch electrically coupled with the first terminal of the first main generator rectifier and a second branch electrically coupled with the first terminal of the second main generator rectifier, the second terminal of the first main generator rectifier and the second terminal of the second main generator rectifier are not electrically coupled with an interphase transformer, and

wherein the first and second three-phase windings are paralleled through the single interphase transformer.

13. The aircraft electrical system of claim 12 , wherein the first and second three-phase windings are configured to operate with full 120 degree conduction in each phase.

14. The aircraft electrical system of claim 12 , wherein the first bridge and the second bridge of the single main generator interphase transformer are electrically coupled with a first DC voltage output, and wherein the second terminal of the first main generator rectifier and the second terminal of the second main generator rectifier are directly electrically coupled with a second DC voltage output without an interphase transformer being positioned therebetween.

15. The aircraft electrical system of claim 12 , wherein the main generator provides DC power output at approximately 270 volts.

16. The aircraft electrical system of claim 12 , wherein the main generator comprises a positive DC power output and a negative DC power output, wherein the aircraft electrical system further comprises an electrical bus, and wherein the positive DC power output and a negative DC power output provide electrical power to the electrical bus of the aircraft electrical system.