Patent ID: 8661779
Filing Date: 2014-03-04
Classification: F23C,F23D,F23R

Abstract:
1. A gas turbine fuel injector for alternate fuels of different energy densities, comprising: first and second main fuel delivery pathways through a main fuel delivery tube structure, through vanes extending radially therefrom, and exiting through respective first and second sets of apertures in exterior surfaces of the vanes, wherein each fuel delivery pathway is configured to independently supply a quantity of fuel sufficient to enable injector operation, and wherein only one fuel delivery pathway is necessary for injector operation; wherein the first main fuel delivery pathway provides a first main fuel flow rate of a first fuel at a given fuel delivery pathway backpressure that is essentially common to both sets of fuel delivery pathway apertures, and the second main fuel delivery pathway provides a second main fuel flow rate of a second fuel that is at least about twice the first main fuel flow rate at the given fuel delivery pathway backpressure due to a lower pressure loss in the second main fuel delivery pathway from greater cross-sectional areas in respective portions of the second main fuel delivery pathway compared to the first main fuel delivery pathways, wherein the second fuel has a lower energy density than the first fuel and wherein within the vanes the second main fuel delivery pathway comprises a radially extending passage comprising a maximum width not greater than a maximum width of a radial extending passage of the first main fuel delivery pathway.