Patent ID: 6968693

Claim:
A reverse flow combustor for a gas turbine, comprising a cylindrical shaped combustor casing comprising an end cap disposed at one end and an open end in fluid communication with the gas turbine; a cylindrical combustor liner disposed in the casing interiorly defining a combustion chamber and exteriorly defining a reverse flow fluid passageway between the casing and the liner; a swirler and mixer assembly upstream from the combustion chamber, wherein the assembly comprises annularly arranged swirler and mixers, wherein each one of the annularly arranged swirler and mixers comprises a centerbody, an inner swirler attached to the centerbody, an outer swirler attached to the inner swirler and a shroud comprising an annularly tapered wall extending between each one of the swirler and mixers and the combustion chamber; a domeplate intermediate the combustion chamber and the swirler and mixer assembly; a primary fuel delivery system comprising a fuel source in fluid communication with each one of the swirler and mixers, wherein the primary fuel system is adapted to radially inject fuel into the outer swirler; and a secondary fuel delivery system comprising a fluid passageway in the annularly tapered wall of the shroud, wherein the fluid passageway is in fluid communication with the fuel source, wherein the primary and secondary fuel delivery system can be independently controlled for each one of the four swirler and mixers.