Patent ID: 6735949
Filing Date: 2004-05-18
Classification: F23C,F23D,F23R

Abstract:
A gas turbine engine combustor can assembly comprising:a combustor can downstream of a pre-mixer; said pre-mixer having a pre-mixer upstream end, a pre-mixer downstream end and a pre-mixer flowpath therebetween, a plurality of circumferentially spaced apart swirling vanes disposed across said pre-mixer flowpath between said upstream and downstream ends, and a primary fuel injection means for injecting fuel into said pre-mixer flowpath; said combustor can having a combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with said pre-mixer; an annular trapped dual vortex cavity located at said upstream end of said combustor liner and defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween; a cavity opening at a radially inner end of said cavity spaced apart from said radially outer wall and extending between said aft wall and said forward wall; air injection first holes in said forward wall and air injection second holes in said aft wall, said air injection first and second holes spaced radially apart; and fuel injection holes in at least one of said forward and aft walls.