Patent ID: 8393891

Claim:
A turbine system, comprising: a mixed fuel-air flow; and a gas turbine engine; wherein the gas turbine engine comprises: a combustion nozzle; wherein the combustion nozzle comprises a center body; a mixed fuel-air flow inlet arranged perpendicularly to an outlet of the center body, the mixed fuel-air inlet in fluid communication with a mixed fuel-air inlet flow channel arranged parallel with a longitudinal axis of the conical body; and a conical nozzle extending from the center body and expanding outwardly therefrom, the mixed fuel-air flow acts to cool a backside of the conical nozzle; the conical nozzle comprising a plurality of apertures positioned therein; wherein the plurality of apertures extends through the conical nozzle and spaced along the length of the conical nozzle in an array such that a fractional flow of the mixed fuel-air flow passes through the plurality of apertures from an exterior of the conical nozzle to an interior of the conical nozzle, wherein a remainder flow of the mixed fuel-air flow passes around the conical nozzle, and wherein the fractional flow burns at a higher equivalence ratio than the remainder flow and the remainder flow expands and recirculates via vortex breakdown of the conical nozzle and burns within the combustion chamber.