Patent ID: 9163584
Filing Date: 2015-10-20
Classification: B64G,F01D,F02C,F02K,F23R,G21D,H05H,Y02E,Y02T

Abstract:
1. A method for supersonic lean fuel combustion comprising the steps of: providing an apparatus comprising: 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; and extracting 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.