Patent ID: 8256226

Claim:
A burner for use in a gas turbine engine, comprising: a burner tube having an inlet end and an outlet end; a plurality of air passages extending axially in the burner tube and configured to convey an air flow from the inlet end to the outlet end; a plurality of fuel passages extending axially and circumferentially in the burner tube and spaced around the plurality of air passages and configured to convey fuel from the inlet end to the outlet end; and a radial air swirler provided at the outlet end configured to direct the air flow radially toward the outlet end and impart swirl to the air flow, the radial air swirler comprising a plurality of vanes to direct and swirl the air flow and an annular end plate downstream of the radial air swirler, wherein the end plate comprises a plurality of fuel injection passages circumferentially spaced and terminating at an inner circumference of the annular end plate to inject the fuel radially into the swirling air flow downstream of the radial air swirler.