초록

The present application provides a combustor for use with a gas turbine engine. The combustor may include a head end with a non-circular configuration, a number of fuel nozzles positioned about the head end, and a transition piece extending downstream of the head end.

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1. A combustor for use with a gas turbine engine, comprising: an elliptical head end positioned at a first end of the combustor, the elliptical head end having an elliptical cross-sectional geometry with a major axis and a minor axis;a plurality of fuel nozzles positioned within the elliptical head

1. A combustor for use with a gas turbine engine, comprising: an elliptical head end positioned at a first end of the combustor, the elliptical head end having an elliptical cross-sectional geometry with a major axis and a minor axis;a plurality of fuel nozzles positioned within the elliptical head end at the first end of the combustor;a transition piece extending downstream of the elliptical head end, the transition piece comprising the elliptical cross-sectional geometry at a first transition piece end and a non-circular configuration at a second transition piece end, the non-circular configuration is different than the elliptical cross-sectional geometry; andthe plurality of fuel nozzles comprises an arrangement of at least 4 fuel nozzles arranged in an array parallel to the major axis of the elliptical cross-sectional geometry. 2. The combustor of claim 1, wherein the combustor comprises a can combustor. 3. The combustor of claim 1, wherein the plurality of fuel nozzles are positioned within a cap about the elliptical head end. 4. The combustor of claim 3, wherein the cap comprises an elliptical cap. 5. The combustor of claim 1, wherein the transition piece comprises an elliptical transition piece. 6. The combustor of claim 1, wherein the second transition piece end is an aft end that comprises the non-circular configuration. 7. The combustor of claim 1, wherein the transition piece extends to a turbine stage. 8. The combustor of claim 1, further comprising an impingement sleeve surrounding the transition piece. 9. A can combustor for use with a gas turbine engine, comprising: an elliptical head end positioned at a first end of the combustor, the elliptical head end having an elliptical cross-sectional geometry with a major axis and a minor axis;a plurality of fuel nozzles positioned within the elliptical head end at the first end of the combustor;an integrated piece extending downstream of the elliptical head end, the integrated piece comprising an elliptical cross-sectional geometry configured to mate with the elliptical head end, and a non-circular configuration at an aft end of the integrated piece, the non-circular configuration different from the elliptical cross-sectional geometry; andthe plurality of fuel nozzles comprises an arrangement of at least 4 fuel nozzles arranged in an array parallel to the major axis of the elliptical cross-sectional geometry, wherein the plurality of fuel nozzles are positioned within an elliptical cap about the elliptical head end. 10. A one-piece can combustor for use with a gas turbine engine, comprising: an elliptical head end positioned at a first end of the combustor, the elliptical head end having an elliptical cross-sectional geometry with a major axis and a minor axis;a plurality of fuel nozzles positioned within the elliptical head end at the first end of the combustor;an aft end;an integrated piece extending downstream of the elliptical head end to the aft end, the integrated piece comprising the elliptical cross-sectional geometry configured to mate with the elliptical head end, and a non-circular configuration at the aft end, the non-circular configuration different from the elliptical cross-sectional geometry;a turbine stage positioned about the aft end; andthe plurality of fuel nozzles comprises an arrangement of at least 4 fuel nozzles arranged in an array parallel to the major axis of the elliptical cross-sectional geometry. 11. The one-piece can combustor of claim 10, wherein the plurality of fuel nozzles are positioned within a cap about the elliptical head end. 12. The one-piece can combustor of claim 11, wherein the cap comprises an elliptical cap.