FUEL NOZZLE FOR AXIALLY STAGED FUEL INJECTION

摘要

The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular ring connectedly surrounding the plurality of vanes. Fuel is directed through the core and then through the vanes and is injected at different axial planes generally perpendicular to an oncoming air stream to obtain a broad spectrum of gas residence time between the point of fuel injection and the flame.

主权项

1. A fuel nozzle assembly for a gas turbine combustor comprising a swirler having a plurality of vanes extending radially outward from a core, each of the plurality of vanes having:
a plurality of apertures staggered at different axial planes along each vane, each of the plurality of apertures connected to a passageway within each vane; an appendage extending from each of the vanes and comprising a trailing edge and a curved portion upstream of the trailing edge; and, a trunk portion extending forward and having a rounded leading edge extending radially outward from proximate a front flange of the core to a radially outer surface of the vane.