DUAL FUEL NOZZLE WITH CONCENTRIC FUEL PASSAGES FOR A GAS TURBINE ENGINE

摘要

A fuel nozzle is provided for a combustor of a gas turbine engine. The fuel nozzle includes an outer air swirler along an axis. The outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler. An annular liquid passage is defined between the inner air swirler and an air inflow tube. A tube is within a housing to define an annular gas passage around the tube. The tube is operable to communicate a liquid into the annular liquid passage and the annular gas passage is operable to communicate a gas into the annular fuel gas passage.

主权项

1. A fuel nozzle for a combustor of a gas turbine engine, comprising:
an outer air swirler along an axis, the outer air swirler defines an outer annular air passage; an inner air swirler along the axis to define an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, wherein an annular liquid passage is defined between the inner air swirler and an air inflow tube; and a tube within a housing to define an annular gas passage around the tube, the tube operable to communicate a liquid into the annular liquid passage and the annular gas passage operable to communicate a gas into the annular fuel gas passage.