A fuel nozzle and a combustor for a gas turbine

摘要

A fuel nozzle 24 for a gas turbine 10 includes an annular passage 30 configured to flow a fuel and a disk 32 concentric with and disposed at a second end 40 of the annular passage 30. The disk 32 extends radially outward from the second end 40. A plurality of passages 50 extend through the disk 32 and are configured to impart swirl to a working fluid flowing through the passages 50. A shroud 34 including an upstream end 52 axially separated from a downstream end 54 surrounds the disk 32 and extends downstream from the disk 32.