HYBRID PREFILMING AIRBLAST, PREVAPORIZING, LEAN-PREMIXING DUAL-FUEL NOZZLE FOR GAS TURBINE COMBUSTOR

摘要

PROBLEM TO BE SOLVED: To provide a dual-fuel nozzle for a gas turbine combustor.;SOLUTION: The 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 42. The fuel jets 44 are oriented to eject liquid fuel radially outward from the hub 42. An annular air passage 3 includes a swirler 2 that imparts a swirl to air flowing in the annular air passage 3, and a splitter ring is disposed in the annular air passage 3 and surrounds the plurality of liquid fuel jets 44. The nozzle injects liquid fuels into a swirling annular airstream and then atomizes, disperses and vaporizes the fuels in a lean premixing dual fuel nozzle for a gas turbine combustor.;COPYRIGHT: (C)2012,JPO&INPIT