Patent ID: 9291103
Filing Date: 2016-03-22
CPC Classification: F02C,F23R

Claim Text:
1. A fuel nozzle for a gas turbine, comprising: a. a main body, the main body having an upstream end axially separated from a downstream end, the upstream end including a flange formed to mount to an end cover of a combustor, the main body at least partially defining a fuel supply passage that extends through the upstream end and at least partially through the main body; b. a fuel distribution manifold disposed at the downstream end of the main body, the fuel distribution manifold having a plurality of axially extending passages that extend through the fuel distribution manifold; c. a plurality of axially extending tubes, each tube coaxially aligned with and extending axially downstream from a respective one of the plurality of axially extending passages, each tube having a respective upstream end seated within the fuel distribution manifold and axially offset from an upstream end of the fuel distribution manifold; and d. a first plurality of fuel injection ports, each fuel injection port of the first plurality of fuel injection ports defining a flow path between the fuel supply passage and a respective one of the plurality of axially extending passages.