Patent Number: 
Section: claims

1. An apparatus for conditioning flow in a gas flow turbine vehicle engine comprising: a gas flow turbine engine having an engine inlet,  an annular shaped inlet flow passage having a inner wall and outer wall and being located upstream relative to the gas flow of the engine inlet and including a magnet to create a magnetic field operative across the flow passage, and  at least one electron beam generator which includes one or more slots that define a spiral on one or both of the inner wall and the outer wall through which electron beams pass to form a locally ionized auger-shaped region within the flow passage. 2. A flow conditioning flow apparatus as set forth in  claim 1 , wherein said magnet comprises a superconducting magnet. claim 1 3. A flow conditioning flow apparatus as set forth in  claim 2 , wherein said magnetic field is a radial field. claim 2 4. A flow conditioning flow apparatus as set forth in  claim 3 , further comprising a power extraction device. claim 3 5. A flow conditioning flow apparatus as set forth in  claim 4 , wherein said power extraction device comprises an electrical load placed across the inlet and outlet of the flow passage which is used to extract power. claim 4 6. A flow conditioning flow apparatus as set forth in  claim 5 , wherein said extracted power is used for the reduction of drag of said vehicle. claim 5 7. A method of conditioning flow upstream of the inlet of a gas flow turbine vehicle engine comprising the use of a magnetic flow interaction in a non-conducting fluid rendered conductive by electromagnetic means and thereby to modify the flow characteristics of the fluid, said magnetic flow interaction taking place within an annular flow passage having a cylindrical inner wall and a cylindrical outer wall together defining a flow path, and including one or more magnets to create a magnetic field operative across the flow passage and at least one electron beam generator directed within said magnetic field which passes one or more electron beams through one or more slots which define a spiral in the inner wall or the outer wall to form a locally ionized regions that spirals down the flow path. 8. A method as set forth in  claim 7 , wherein said annular flow passage includes an inlet and an outlet and wherein an electrical load is placed across the inlet and outlet of the annular flow path to extract power. claim 7 9. A method as set forth in  claim 8 , wherein said electrical load is used to extract power and recycle it to drive a jet aircraft powered by said gas turbine. claim 8 10. A method as set forth in  claim 9 , wherein said extracted power is used for the reduction of drag of said vehicle. claim 9 11. A method as set forth in  claim 7 , wherein said magnet comprises a superconducting magnet. claim 7 12. A method as set forth in  claim 11 , wherein said magnetic field is a radial field. claim 11 13. A method as set forth in  claim 12 , further comprising a power extraction device. claim 12 14. An aircraft engine for high altitude flight comprising: a gas flow turbine engine having an engine inlet,  an annular flow passage having an inner cylindrical wall and an outer cylindrical wall and being located upstream relative to the gas flow of the engine inlet and including a superconducting magnet to create a radial magnetic field operative across the flow passage, and  at least one electron beam generator including one or more slots which form a spiral in either or both of the inner and the outer wall through which one or more electron beams is passed to form a locally ionized region within the flow passage. 15. An aircraft engine as set forth in  claim 14 , wherein said magnetic field is a radial field. claim 14 16. An aircraft engine as set forth in  claim 15 , further comprising a power extraction device. claim 15 17. An aircraft engine as set forth in  claim 16 , wherein said power extraction device comprises an electrical load placed across the inlet and outlet of the flow passage. claim 16 18. An aircraft engine as set forth in  claim 17 , wherein said electrical load is used to extract power and recycle it to drive an aircraft powered by said aircraft engine. claim 17 19. An aircraft engine as set forth in  claim 18 , wherein said electrical load is used to influence the thermodynamic characteristics of the drive system of the aircraft. claim 18 20. A method of increasing the operating speed of an aircraft having a gas combustion engine which comprises conditioning the flow within the gas combustor of the engine and using an electromagnetic flow interaction in a non-conducting fluid to render it conductive and thereby to modify the flow characteristics of the fluid, said electromagnetic flow interaction taking place within an annular flow passage having and inner wall and an outer wall and an inlet and an outlet and defining a flow path, and including one or more superconducting magnets to create a radial magnetic field operative across the flow passage and locally ionized regions which comprise a flat profile of electron distribution that extends radially from the inner wall to the outer wall and that spirals down the flow passage. 21. A method as set forth in  claim 20 , wherein at least two electron beam generators are used in opposition to each other across the flow passage to form the electron distribution. claim 20 22. A method of increasing the operating speed of an aircraft engine as set forth in  claim 20 , further comprising a power extraction device comprising an electrical load placed across the inlet and the outlet of the flow passage wherein the electrical load is used to extract kinetic energy to reduce the temperature that gas enters the combustor. claim 20 23. A method of increasing the operating speed of an aircraft as set forth in  claim 20 , further comprising softening the shock wave on the aircraft. claim 20 24. A device for conditioning flow in a gas flow turbine vehicle engine comprising: a gas flow turbine engine having an engine inlet,  an annular inlet flow passage having an inner wall and an outer wall and located upstream of the engine inlet relative to the gas flow and including a magnet to create a magnetic field operative across the flow passage; and  locally ionized regions which comprise a flat profile of electron distribution that extends radially from the inner wall to the outer wall and that spirals down the flow passage. 25. An aircraft engine for high altitude flight comprising: a gas flow turbine engine having an engine inlet,  an annular inlet flow passage having an inner wall and an outer wall and located upstream relative to the gas flow of the engine inlet and including a superconducting magnet to create a radial magnetic field operative across the flow passage; and  locally ionized regions which comprise a flat profile of electron distribution that extends radially from the inner wall to the outer wall and that spirals down the flow passage.