Patent Number: 
Section: claims

1. A method for supersonic lean fuel combustion comprising the steps of:providing an apparatus comprising:a plasma arc torch comprising:a cylindrical vessel having a first end and a second end,a tangential inlet connected to or proximate to the first end of the cylindrical vessel,a tangential outlet connected to or proximate to the second end of the cylindrical vessel,an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, anda hollow electrode nozzle connected to the second end of the cylindrical vessel such that a center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel,a cyclone combustor connected to the hollow electrode nozzle of the plasma arc torch, wherein the cyclone combustor has a tangential entry, a tangential exit, and an exhaust outlet, anda turbocharger having a turbine connected to a compressor via a shaft, wherein a turbine entry is connected to the tangential exit of the cyclone combustor, a compressor exit is connected to the tangential entry of the cyclone combustor;generating a vortex within the cylindrical vessel of the plasma arc torch by injecting a gas, fluid or steam into the tangential inlet of the plasma arc torch such that a portion of the gas, fluid or steam discharges out of the tangential outlet of the plasma arc torch;creating an electric arc between the electrode and the hollow electrode nozzle to generate a plasma that is confined by the vortex and is discharged through the hollow electrode nozzle into the cyclone combustor;generating a combustion air whirl flow within the cyclone combustor by injecting a compressed air into the tangential entry of the cyclone combustor;converting a fuel to one or more hot gases using the plasma; andextracting a rotational energy from at least a portion of the one or more hot gases that pass from the tangential exit of the cyclone combustor into the turbine entry using the turbine of the turbocharger. 2. The method as recited in claim 1, further comprising a first valve disposed between the tangential exit of the cyclone combustor and the turbine entry. 3. The method as recited in claim 1, further comprising a compressor inlet valve connected to a compressor entry of the compressor. 4. The method as recited in claim 3, wherein the compressor inlet valve comprises:a volute with a tangential entry;a cone-shaped reducer connected to the volute;a linear actuator connected to the volute,a cone-shaped stopper disposed within the cone-shaped reducer and operably connected to the linear actuator;a controller connected to the linear actuator; andadjusting a gap between the cone-shaped stopper and the cone-shaped reducer using the controller to increase or decrease a mass flow while maintaining a whirl velocity to closely match a compressor tip velocity. 5. The method as recited in claim 1, further comprising:a first stage recuperator connected to a discharge exhaust of the turbine and the compressor exit;a second stage recuperator connected to a discharge exhaust of the cyclone combustor;heating a compressed air from the compressor using the one or more hot gases within first stage recuperator and the second stage recuperator; andintroducing the compressed air into the cyclone combustor via the tangential entry of the cyclone combustor. 6. The method as recited in claim 5, further comprising a second valve disposed between the discharge exhaust of the cyclone combustor and the second stage recuperator. 7. The method as recited in claim 1, further comprising a pinon gear attached to the shaft between the turbine and the compressor. 8. The method as recited in claim 7, further comprising a bull gear and a drive shaft connected to the pinion gear. 9. The method as recited in claim 8, further comprising a motor generator connected to the drive shaft. 10. The method as recited in claim 8, further comprising a high bypass fan connected to the drive shaft. 11. The method as recited in claim 8, further comprising a propeller connected to the drive shaft. 12. The method as recited in claim 1, wherein the first electrode is hollow and further comprising the step of introducing a fuel into the hollow first electrode. 13. The method as recited in claim 1, further comprising the step of introducing a fuel into the tangential inlet of the plasma arc torch. 14. The method as recited in claim 1, further comprising the step of introducing the fuel into the plasma that discharges through the hollow electrode nozzle.