FUEL NOZZLE AND COMBUSTOR FOR GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To provide a fuel nozzle and combuster for a gas turbine.SOLUTION: A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart swirl to a working fluid flowing through the passages. A shroud including an upstream end axially separated from a downstream end surrounds the disk and extends downstream from the disk.