Patent ID: 9217570
Filing Date: 2015-12-22
Classification: F23D,F23L,F23R

Abstract:
1. An axial flow fuel nozzle for a gas turbine, the axial flow fuel nozzle comprising: an annular air passage configured to receive compressor discharge air; a plurality of swirler vane slots positioned adjacent a downstream axial end of the annular air passage, closer to the downstream axial end than an upstream axial end; a first annular passage disposed radially inward of the annular air passage and including first openings positioned adjacent an axial end of the first annular passage and downstream of the plurality of swirler vane slots; a second annular passage disposed radially inward of the first annular passage and including second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings; and a nozzle center body cooperable with the first and second annular passages, the nozzle center body terminating downstream of the first openings and the second openings, wherein the first annular passage is coupled with one of a source of liquid fuel and a source of mixed liquid fuel and water, and wherein the second annular passage is coupled with a source of water.