Patent ID: 6865889

Claim:
A combustor for a gas turbine comprising: a pilot mixer comprising an air splitter, a pilot fuel nozzle, and a plurality of axial air swirlers upstream from said pilot fuel nozzle, said air splitter downstream from said pilot fuel nozzle, said air swirlers radially outward from and concentrically mounted with respect to said pilot fuel nozzle; a main mixer radially outward from and concentrically aligned with respect to said pilot mixer, said main mixer comprising a plurality of fuel injection ports and a swirler comprising at least one of a conical air swirler and a cyclone air swirler, said main mixer swirler upstream from said main mixer fuel injection ports; and an annular centerbody extending between said pilot mixer and main mixer, said centerbody comprising a radially inner surface comprising a divergent portion, an aft portion, and a lip extending outwardly therebetween.