Patent ID: 9677766
Date: 2017-06-13
CPC Classifications: F23D,F23R

Claim:
1. A fuel nozzle for use in a turbine engine comprising: a nozzle body; a liquid fuel injector configured to discharge liquid fuel therefrom; and a plurality of premixer tubes defined within and extending through said nozzle body, each of said plurality of premixer tubes coupled in flow communication with said liquid fuel injector and configured to receive a flow of liquid fuel and a flow of air at an upstream end of said plurality of premixer tubes, wherein the flow of liquid fuel and the flow of air in each premixer tube are progressively mixed as the flow of liquid fuel and the flow of air are channeled through each premixer tube, wherein said liquid fuel injector comprises a plurality of fuel spokes that each comprises a hollow tube that are straight and having a plurality of injection ports defined therein that are each configured to discharge liquid fuel therefrom, and each said injection port substantially coaxially aligns with a corresponding premixer tube centerline axis and is configured to direct a liquid fuel jet substantially axially into said corresponding premixer tube, wherein each liquid fuel jet comprises a discharge angle of 5° to 15° with respect to the corresponding premixer tube centerline axis, wherein said plurality of fuel spokes extend through said nozzle body and through said plurality of premixer tubes substantially perpendicularly with respect to the centerline axes of the plurality of premixer tubes.