Axial flow fuel nozzle with a stepped center body

摘要

An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage (62) receives compressor discharge air, and a plurality of swirler vane slots (64) are positioned adjacent an axial end of the annular air passage (62). A first next annular passage (66) is disposed radially inward of the annular air passage (62) and includes first openings (68) positioned adjacent an axial end of the first annular passage (66) and downstream of the swirler vane slots (64). A second next annular passage (70) is disposed radially inward of the first annular passage (66) and includes second openings (72) positioned adjacent an axial end of the second annular passage (70) and downstream of the first openings (68).