Combustor with non-circular head end

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; and

the 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; and

the 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; and

the 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.