Abstract: An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.

Abstract: A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. 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 includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.

Abstract: A fuel nozzle centerbody is provided that includes a cylindrical cross-sectional area, and a baffle co-axially aligned within the centerbody. The baffle includes a plurality of circumferentially-spaced apertures configured to channel an airflow radially outward such that the channeled airflow impinges a centerbody inner surface.

Abstract: A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides.

Abstract: A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. 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 includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.

Abstract: A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides.

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.

Abstract: A gas turbine engine fuel nozzle assembly has concentric primary and secondary pilot fuel nozzles with circular primary and annular secondary exits respectively and a main fuel nozzle spaced radially outwardly of the pilot fuel nozzles. The primary and secondary pilot fuel nozzles include conical primary and secondary exit holes respectively. The secondary pilot fuel nozzle is located directly adjacent to and surrounding the primary pilot fuel nozzle. Alternatively the secondary pilot fuel nozzle may be radially spaced apart from the primary pilot fuel nozzle. A fuel injector having a hollow stem may be used to support the fuel nozzle assembly. A first pilot swirler may be located radially outwardly of and adjacent to the dual orifice pilot fuel injector tip, a second pilot swirler located radially outwardly of the first swirler, and a splitter radially positioned between the first and second pilot swirlers.

Abstract: A fuel nozzle centerbody is provided that includes a cylindrical cross-sectional area, and a baffle co-axially aligned within the centerbody. The baffle includes a plurality of circumferentially-spaced apertures configured to channel an airflow radially outward such that the channeled airflow impinges a centerbody inner surface.