Patent ID: 9383098
Filing Date: 2016-07-05
CPC Classification: F23D,F23R

Claim Text:
1. A radial flow fuel nozzle for a combustor of a gas turbine, comprising: a. a fuel distribution manifold shaped as a ring and having a bottom side wall axially spaced from a top side wall, wherein the bottom side wall defines at least one inlet that provides for fuel flow into the fuel distribution manifold and the to side wall defines a plurality of outlets circumferentially spaced about the top side wall; b. a fuel injection manifold shaped as a ring and axially separated from and coaxially aligned with the fuel distribution manifold, the fuel injection manifold having an inner side portion radially spaced from an outer side portion, a bottom side portion axially spaced from a top side portion and perpendicular to the outer side portion and a plurality of circumferentially spaced fuel ports that extend through the outer side portion, wherein the bottom side portion defines a plurality of inlets circumferentially spaced about the bottom side portion; and c. a plurality of circumferentially spaced tubes that extend axially from the top side wall of the fuel distribution manifold to the bottom side portion of the injection manifold, wherein the plurality of circumferentially spaced tubes is annularly arranged about an axial centerline of the radial flow fuel nozzle, each tube of the plurality of circumferentially spaced tubes defining a respective fluid communication path between a respective outlet of the plurality of outlets of the fuel distribution manifold and a respective inlet of the plurality of inlets of the fuel injection manifold.