Integrated hybrid propulsion system

1. A hybrid propulsion system comprising:

a gas generator section comprising a high-pressure compressor;

an electrical power generator section disposed upstream of the gas generator section and configured to be driven by a power turbine;

an output power shaft mated to the power turbine and extending through a central axis of the gas generator section and the power generator section;

an engine enclosure, wherein the engine enclosure is configured to circumferentially surround the power generator section; and

a shroud disposed between the power generator section and the engine enclosure, wherein the shroud comprises non-magnetic material;

wherein the power generator section comprises:

a low pressure compressor comprising at least three axial-flow compressor stage rotating members arranged along the output power shaft, and wherein each of the at least three axial-flow compressor stage rotating members includes a magnetic portion; and

a conducting element mounted within the engine enclosure;

wherein rotation of the at least three axial-flow compressor stage rotating members relative to the conducting element generates a current transmissible by one or more coupled power output cables;

wherein the output power shaft is disposed concentrically within a turbine shaft located in the gas generator section, the output power shaft being structured to extend entirely through the gas generator section and the power generator section;

wherein the shroud is configured to reduce a clearance between the at least three rotating members and the engine enclosure, and wherein the shroud is disposed between the conducting element and the at least three axial-flow compressor stage rotating members.

2. The system of claim 1 , wherein each of the at least three axial-flow compressor stages is driven by the output power shaft, which is coupled to the power turbine located downstream of the gas generator section.

3. The system of claim 1 , wherein:

each of the at least three axial-flow compressor stages comprises a plurality of blades;

the magnetic portion is formed by at least a subset of the plurality of blades; and

each of the subset of the plurality of blades is made of one or more magnetic alloys.

4. The system of claim 1 , wherein:

each of the at least three axial-flow compressor stages comprise a plurality of blades;

the magnetic portion is formed by at least a subset of the plurality of blades; and

each of the subset of the plurality of blades includes a permanent magnet embedded within a tip portion of each blade such that only the subset of the plurality of blades is magnetized.

5. The system of claim 1 , wherein the conducting element is integrally formed within the engine enclosure.

6. The system of claim 1 , wherein the shroud comprises non-magnetic metallic or non-magnetic composite material.

7. The system of claim 1 , wherein the conducting element includes one or more conductive coils.

8. A hybrid propulsion system comprising:

a gas generator section comprising a high-pressure compressor;

an electrical power generator section disposed upstream of the gas generator section and configured to be driven by a power turbine;

an output power shaft mated to the power turbine and extending through a central axis of the gas generator section and the electrical power generator section;

an engine enclosure, wherein the engine enclosure is configured to circumferentially surround at least the power generator section, and includes a conductive portion comprising a plurality of coils; and

a shroud disposed between the power generator section and the engine enclosure, wherein the shroud comprises non-magnetic material;

wherein the power generator section comprises:

a low pressure compressor comprising at least three axial-flow compressor stages arranged along the output shaft and configured to rotate about an axis defined by the output power shaft, wherein each of the at least three axial-flow compressor stages includes a plurality of blades, a magnetic portion, and a non-magnetic portion; and

wherein rotation of the at least three axial-flow compressor stages relative to the engine enclosure generates a current transmissible by one or more power output cables coupled to the engine enclosure; and

wherein the output power shaft is disposed concentrically within a turbine shaft located in the gas generator section, the output power shaft being structured to extend entirely through the gas generator section and the power generator section; and

wherein the shroud is configured to reduce a clearance between the at least three axial-flow compressor stages and the engine enclosure, and wherein the shroud is disposed between the conductive portion and the axial-flow compressor stages.

9. The system of claim 8 , wherein the magnetic portion is formed by at least a subset of the plurality of blades, and wherein each of the subset of the plurality of blades is made of one or more magnetic alloys.

10. The system of claim 8 , wherein the magnetic portion is formed by at least a subset of the plurality of blades, and wherein each of the subset of the plurality of blades includes a permanent magnet embedded within a tip portion of each blade.

11. The system of claim 8 , wherein the conductive portion is mounted to an inner surface of the engine enclosure.

12. The system of claim 8 , wherein the engine enclosure comprises a non-magnetic section, wherein the non-magnetic section surrounds the power generator section.

13. The system of claim 12 , wherein the non-magnetic section of the engine enclosure comprises at least one of a graphite epoxy composite or a nickel chromium alloy.

14. A hybrid propulsion system comprising:

a gas generator section comprising a high-pressure compressor;

an electrical power generator section disposed upstream of the gas generator section and configured to be driven by a power turbine;

an output power shaft mated to the power turbine and extending through a central axis of the gas generator section and the power generator section; and

an engine enclosure, wherein the engine enclosure is configured to circumferentially surround the power generator section;

wherein the power generator section comprises:

one or more disc-shaped flux rotors mated to the output power shaft and configured to rotate with the output power shaft about an axis defined by the output power shaft; and

at least one disc-shaped flux stator disposed adjacent at least one of the one or more disc-shaped flux rotors

wherein each of the disc-shaped flux rotors includes a magnetic portion and a non-magnetic portion;

wherein the magnetic portion of each of the disc-shaped flux rotors generates a current within a stationary conductor portion when each of the disc-shaped flux rotors rotates about the axis relative to the engine enclosure;

wherein a speed of rotation of the one or more disc-shaped flux rotors is regulated by a load requirement;

wherein the output power shaft is disposed concentrically within a turbine shaft located in the gas generator section, the output power shaft being structured to extend entirely through the gas generator section and the power generator section; and

wherein the stationary conductor portion comprises the least one disc-shaped flux stator disposed adjacent at least one of the one or more disc-shaped flux rotors, and wherein the at least one disc-shaped flux stator is coaxial with the one or more disc-shaped flux rotors.

15. The system of claim 14 , wherein the at least one disc-shaped flux stator is coupled to the engine enclosure.

16. The system of claim 14 , wherein the engine enclosure transmits the current generated within the stationary conductor portion via one or more coupled output cables.

17. The system of claim 14 , further comprising a variable load coupled to the power generator section, wherein the variable load is configured to fulfill a minimum load requirement.

18. The system of claim 14 , wherein the magnetic portion comprises a plurality of circumferentially arranged permanent magnets.