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With turbine segments controlled electrically in a shaftless design, the turbine of the present invention creates high propulsion efficiencies over a broader range of operating conditions through the integration of gas turbine, electric and magnetic power systems, advanced materials and alternative

With turbine segments controlled electrically in a shaftless design, the turbine of the present invention creates high propulsion efficiencies over a broader range of operating conditions through the integration of gas turbine, electric and magnetic power systems, advanced materials and alternative petroleum-based combustion cycles.

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1. A system for operating a jet turbine engine, said system comprising: a compressor for receiving an intake airflow to the jet engine;a hypersonic compression ram radially inward of the compressor for receiving another portion of the intake airflow;a combustion chamber fluid communication with the

1. A system for operating a jet turbine engine, said system comprising: a compressor for receiving an intake airflow to the jet engine;a hypersonic compression ram radially inward of the compressor for receiving another portion of the intake airflow;a combustion chamber fluid communication with the compressor and the hypersonic compression ram;a turbine having a plurality of turbine components, wherein a plurality of coils are disposed about a perimeter of said turbine for generating electricity to supply to the jet engine; andan electric controller for controlling said turbine. 2. The system of claim 1, wherein at least one of said plurality of turbine components comprises a ceramic matrix. 3. The system of claim 2, wherein at least one of said plurality of turbine components comprises a hafnium carbide fiber reinforced ceramic matrix. 4. The system of claim 2, wherein said plurality of turbine components comprise any of stators, turbine blades, diffuser stators, shroud segments, and turbine discs. 5. The system of claim 1, wherein at least one of said plurality of turbine components comprises continuous ceramic reinforcement fiber. 6. The system of claim 4, wherein said plurality of turbine components comprise compressor vanes. 7. The system of claim 4, wherein said plurality of turbine components comprise diffuser stators. 8. The system of claim 4, wherein said plurality of turbine components comprise turbine blades. 9. The system of claim 4, wherein said plurality of turbine components comprise a ceramic matrix. 10. The system of claim 9, wherein said plurality of turbine components comprise a hafnium carbide fiber reinforced ceramic matrix. 11. The system of claim 9, wherein said plurality of turbine components comprise continuous ceramic reinforcement fiber. 12. A system for operating a jet turbine engine, said system comprising: a shaftless turbine having an outer casing and a selectively accessible hollow interior portion radially inward of the shaftless turbine and configured to allow combustion flow to bypass the shaftless turbine;an electric controller for controlling said shaftless turbine;a main compressor;a diffuser;a plurality of turbine components, andwherein said compressor, said diffuser and said plurality of turbine components operate in dynamic compression within the outer casing of the shaftless turbine. 13. A system for operating a jet turbine engine, said system comprising: a shaftless turbine having an outer casing;a hypersonic exhaust duct radially inward of the shaftless turbine and configured to selectively allow combustion flow to bypass the shaftless turbine;an electric controller for controlling said shaftless turbine;a compressor;a diffuser;a combustor;a turbine generator; and wherein the electric controller operably controls rotational characteristics of the compressor independent of rotational characteristics of one of the diffuser and the turbine generator. 14. The system of claim 13, wherein the electric controller operably controls the rotational characteristics of the diffuser independent of the rotational characteristics of the turbine generator. 15. The system of claim 13, wherein the compressor comprises a plurality of compressor stages and wherein the electric controller operably controls rotational characteristics of a first compressor stage independent of rotational characteristics of a second compressor stage. 16. The system of claim 15, wherein the first compressor stage and the second compressor stage are adjacent within the compressor. 17. The system of claim 13, wherein the compressor comprises a plurality of compressor stages, each stage comprising a rotor assembly and a stator assembly. 18. The system of claim 17, wherein the electric controller operably controls rotational characteristics of the rotor assembly of a compressor stage independent of rotational characteristics of the stator assembly of the same compressor stage. 19. A method of operating a turbine engine comprising: (A) providing a shaftless engine comprising:i) a generally cylindrical frame with interior and exterior surfaces,ii) a plurality of shaftless turbine blade assemblies movable relative to the interior surface of the cylindrical frame, andiii) a plurality of induction coils disposed about a perimeter of the cylindrical frame;(B) creating a combustion event;(C) converting kinetic energy from the combustion event into rotational motion of at least one shaftless turbine blade assembly relative to the interior surface of the cylindrical frame by exposing the at least one shaftless turbine blade assembly to the combustion event; and(D) converting mechanical energy from the rotational motion of the at least one shaftless turbine blade assembly into electrical energy by inducing an electric current in the induction coils with a magnetic field. 20. The method of claim 19 wherein at least a portion of the blade assembly comprises a magnetic material and wherein (D) comprises: (D1) exposing the induction coils to the magnetic fields generated by the shaftless turbine blade assembly. 21. A method of operating a turbine engine comprising: (A) providing a shaftless engine comprising:i) a generally cylindrical frame with an interior surface,ii) a plurality of shaftless turbine blade assemblies movable relative to the interior surface of the cylindrical frame, andiii) a plurality of induction coils disposed about a perimeter of the cylindrical frame;(B) inducing an electric current in the induction coils to create a magnetic field;(C) exposing at least one of the shaftless turbine blade assemblies to the magnetic field; and(D) converting electrical energy from the magnetic field incident on the shaftless turbine blade assembly into rotational motion of a compressor blade assembly relative to the interior surface of the cylindrical frame. 22. The method of claim 21 wherein at least a portion of the shaftless turbine blade assembly comprises a magnetic material.