Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor

摘要

A dual fuel nozzle for a gas turbine combustor includes a hub (42) defining a fuel inlet and a plurality of liquid fuel jets (44) disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage (3) includes a swirler (2) that imparts swirl to air flowing in the annular air passage, and a splitter ring (40) is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.