Patent ID: 6862889
Filing Date: 2005-03-08
Classification: F23R

Abstract:
1. A combustor for a gas turbine comprising: a combustion chamber; a pilot mixer comprising a pilot centerbody and at least one axial air swirler radially outward from and concentrically mounted with respect to said pilot centerbody, said pilot mixer upstream from said combustion chamber; a main mixer radially outward from and concentrically aligned with respect to said pilot mixer, said main mixer comprising at least one swirler configured to inject fuel therethrough into said main mixer, said main mixer upstream from said combustion chamber; and an annular centerbody extending between said pilot mixer and said main mixer, said centerbody comprising a radially inner surface, a radially outer surface, and a plurality of fuel injection ports, said radially inner surface comprising at least one of a divergent portion and a convergent portion, said plurality of fuel injection ports configured to inject fuel radially outwardly into said main mixer.