Patent ID: 9599022
Date: 2017-03-21
CPC Classifications: F02C,F23R,Y10T

Claim:
1. A modular fuel nozzle tip for a gas turbine engine, the modular fuel nozzle tip comprising: a fuel conveying body defining one or more fuel conveying passages extending between an inlet end and an outlet end of the fuel conveying body, the outlet end of the fuel conveying body having a head portion having web portions extending radially therefrom, and at least two projections extending from an end of said web portions, the at least two projections circumferentially spaced apart by slots and collectively defining a circumferentially-interrupted peripheral end surface; an annular cap circumscribing only the outlet end of the fuel conveying body and having a radially inner shoulder surface interfacing with the circumferentially-interrupted peripheral end surface of the fuel conveying body, the radially inner shoulder surface of the annular cap and the slots of the at least two projections defining therebetween a plurality of air channels extending through the head portion of the modular fuel nozzle tip; and two or more fasteners fastening the annular cap to the fuel conveying body and being circumferentially distributed about the annular cap, at least two of the two or more fasteners being diametrically opposed to each other, each of the at least two of the two or more fasteners extending through the annular cap and into one of the at least two projections, the at least two of the two or more fasteners extending radially through two corresponding diametrically opposed holes formed in the annular cap and the at least two projections of the fuel conveying body.