Patent ID: 6550251
Filing Date: 2003-04-22
Classification: F23R

Abstract:
A swirl cup for a gas turbine combustor comprising:a tubular body having an inlet at one end for receiving a fuel injection nozzle to inject fuel into said body, an outlet at an opposite axial end for discharging said fuel into said combustor, and an annular septum axially therebetween; a row of first swirl vanes attached to said septum adjacent said body inlet for channeling into said body air in a first swirl direction around said injected fuel; and a row of second swirl vanes attached to said septum adjacent said first swirl vanes and spaced upstream from said body outlet for channeling into said body additional air in a second swirl direction directly around both said injected fuel and said first swirl air without a flow barrier therebetween; wherein said septum terminates axially between said first and second swirl vanes for allowing direct contact between said air discharged therefrom; and wherein said first and second swirl vanes are inclined radially inwardly to swirl said air radially inwardly and circumferentally around said injected fuel.