COOLING FLOWPATH DIRT DEFLECTOR IN FUEL NOZZLE
First Claim
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1. A gas turbine engine fuel nozzle assembly comprising:
- a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer,an axially aftwardly or downstream extending injector cooling flowpath disposed radially outwardly of and surrounding an air pilot swirler,an annular wall section radially disposed between the pilot swirler and an annular cooling flowpath inlet to the injector cooling flowpath,an annular chamfered leading edge of the annular wall section, anda radially inwardly facing conical chamfered surface of the chamfered leading edge.
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Abstract
A fuel nozzle assembly includes a chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler. A radially inwardly facing conical chamfered surface of the chamfered leading edge deflects dirt from cooling flowpath.
75 Citations
15 Claims
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1. A gas turbine engine fuel nozzle assembly comprising:
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a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer, an axially aftwardly or downstream extending injector cooling flowpath disposed radially outwardly of and surrounding an air pilot swirler, an annular wall section radially disposed between the pilot swirler and an annular cooling flowpath inlet to the injector cooling flowpath, an annular chamfered leading edge of the annular wall section, and a radially inwardly facing conical chamfered surface of the chamfered leading edge. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A gas turbine engine fuel nozzle assembly comprising:
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a dual orifice pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer, substantially concentric primary and secondary pilot fuel nozzles in the pilot fuel injector tip, the primary and secondary pilot fuel nozzles having circular primary and annular secondary exits respectively, an inner pilot swirler located radially outwardly of and adjacent to the pilot fuel injector tip, an outer pilot swirler located radially outwardly of the inner swirler, a splitter radially positioned between the first and second pilot swirlers, a pilot housing including a centerbody radially surrounding the pilot mixer, an axially or downstream extending injector cooling flowpath disposed in the pilot housing and radially between a fuel nozzle inner casing and the centerbody, an upstream forward end of the centerbody including an annular chamfered leading edge of the forward end, and a radially inwardly facing conical chamfered surface of the chamfered leading edge. - View Dependent Claims (9, 10, 11, 14, 15)
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12. A gas turbine engine fuel nozzle assembly comprising:
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a dual orifice pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer, substantially concentric primary and secondary pilot fuel nozzles in the pilot fuel injector tip, the primary and secondary pilot fuel nozzles having circular primary and annular secondary exits respectively, an inner pilot swirler located radially outwardly of and adjacent to the pilot fuel injector tip, an outer pilot swirler located radially outwardly of the inner swirler, a splitter radially positioned between the first and second pilot swirlers, a pilot housing including a centerbody radially surrounding the pilot mixer, an axially or downstream extending injector cooling flowpath disposed in the pilot housing and radially between a fuel nozzle inner casing and the centerbody, an upstream forward end of the centerbody including an annular chamfered leading edge of the forward end, and a radially inwardly facing conical chamfered surface of the chamfered leading edge. - View Dependent Claims (13)
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Specification