초록 ▼

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 imping

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.

대표청구항 ▼

1. A fuel nozzle centerbody having a cylindrical cross-sectional area, said centerbody comprising: an inlet;an outlet;a radially outer wall;a radially inner wall;a centerline axis extending from said inlet to said outlet; anda baffle substantially co-axially aligned within said centerbody, said baff

1. A fuel nozzle centerbody having a cylindrical cross-sectional area, said centerbody comprising: an inlet;an outlet;a radially outer wall;a radially inner wall;a centerline axis extending from said inlet to said outlet; anda baffle substantially co-axially aligned within said centerbody, said baffle comprising:a first end portion, an intermediate portion, and a second end portion;a plurality of circumferentially-spaced apertures configured to channel airflow radially outward to impingement cool said centerbody; andan intermediate support extending radially inward from said intermediate portion of said baffle to contact a mounting flange to facilitate supporting said baffle within said centerbody,said second end portion supported by an end wall flange extending from an end wall of the centerbody,wherein cooling fluid is supplied to the baffle through at least one aperture in said radially inner wall axially between the second end portion and the intermediate support. 2. A fuel nozzle centerbody in accordance with claim 1, wherein said baffle comprises: the intermediate portion having a first end and an opposite second end, said intermediate portion comprising a first diameter;the baffle first end portion extending axially from said intermediate portion first end, said baffle first end portion comprising a second diameter, said second diameter greater than said first diameter; andthe baffle second end portion extending from said intermediate portion second end, said baffle second end portion comprising a third diameter, said third diameter less than said first diameter and said second diameter. 3. A fuel nozzle centerbody in accordance with claim 1, wherein said plurality of apertures in said baffle further comprise: at least one row of circumferentially-spaced apertures configured to direct an airflow perpendicular to a centerbody inner surface; andat least one row of circumferentially-spaced apertures configured to direct an airflow obliquely against said centerbody inner surface. 4. A fuel nozzle centerbody in accordance with claim 1, wherein said centerbody end wall comprises a plurality of apertures configured to vent said airflow from within said centerbody. 5. A fuel nozzle assembly in accordance with claim 1, wherein said centerbody outer wall comprises a second plurality of apertures therethrough and configured to channel a second flow of air radially outward from said centerbody. 6. A fuel nozzle assembly in accordance with claim 5, wherein said second plurality of apertures are arranged in at least one grouping positioned on said centerbody outer wall. 7. A fuel nozzle assembly in accordance with claim 5, wherein said second plurality of apertures are circumferentially-spaced about said centerbody outer wall. 8. A gas turbine engine comprising: a fuel nozzle centerbody including a cylindrical cross-section, said centerbody comprising a radially inner wall, a radially outer wall, and a plurality of apertures through the centerbody outer wall, said plurality of apertures configured to channel a flow of air radially outward from said centerbody; anda baffle comprising a first end portion, an intermediate portion, a second end portion, and a plurality of circumferentially-spaced apertures configured to channel airflow radially outward to impingement cool said centerbody, said baffle co-axially aligned within said centerbody and comprising an intermediate support extending radially inward from said intermediate portion of said baffle to contact a mounting flange to facilitate supporting said baffle within said centerbody,said second end portion supported by an end wall flange extending from an end wall of the centerbody,wherein cooling fluid is supplied to the baffle through at least one aperture in said radially inner wall axially between the second end portion and the intermediate support. 9. A gas turbine engine in accordance with claim 8, wherein said plurality of apertures through said centerbody outer wall are oriented such that said airflow is aligned with a swirl direction surrounding said centerbody. 10. A gas turbine engine in accordance with claim 9, wherein said plurality of apertures through said centerbody outer wall are arranged in at least one grouping positioned on said centerbody outer wall. 11. A gas turbine engine in accordance with claim 9, wherein said plurality of apertures through said centerbody outer wall are circumferentially-spaced about said centerbody outer wall. 12. A gas turbine engine in accordance with claim 8, wherein said plurality of circumferentially-spaced apertures in said baffle are configured to channel an airflow radially outward such that said channeled airflow impinges a centerbody inner surface. 13. A gas turbine engine in accordance with claim 12, wherein said baffle further comprises: the intermediate portion having a first end and an opposite second end, said intermediate portion comprising a first diameter;the baffle first end portion extending axially from said intermediate portion first end, said baffle first end portion comprising a second diameter, said second diameter greater than said first diameter; andthe baffle second end portion extending from said intermediate portion second end, said baffle second end portion comprising a third diameter, said third diameter less than said first diameter and said second diameter. 14. A gas turbine engine in accordance with claim 12, wherein said plurality of baffle apertures further comprises: at least one row of circumferentially-spaced apertures configured to direct an airflow perpendicular to said centerbody inner surface; andat least one row of circumferentially-spaced apertures configured to direct an airflow obliquely against said centerbody inner surface.