Patent ID: 6082111
Filing Date: 2000-07-04
Classification: F23R

Abstract:
A gas turbine combustor, comprising: a nozzle housing, said nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing; a main fuel nozzle, said main fuel nozzle having a main fuel injection port and a tip, said main fuel nozzle extending through said nozzle housing and attached to the nozzle housing base, the tip of said main fuel nozzle located downstream of the nozzle housing base; and a main fuel swirler, said main fuel swirler having an axis, swirler vanes, and a downstream end, the axis of said main fuel swirler substantially parallel to said main fuel nozzle, said main fuel swirler surrounding a portion of said main fuel nozzle, the downstream end of said main fuel swirler located downstream of said main fuel injection port and upstream of said main fuel nozzle tip; and the main fuel injection port located downstream of the swirler vanes.