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The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to r

The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end.

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1. A combustion liner comprising: a generally annular body having an inlet end and an opposing outlet end, the generally annular body having an inner surface facing a combustion chamber and an opposing outer surface, the outer surface having a contoured profile proximate the inlet end such that the

1. A combustion liner comprising: a generally annular body having an inlet end and an opposing outlet end, the generally annular body having an inner surface facing a combustion chamber and an opposing outer surface, the outer surface having a contoured profile proximate the inlet end such that the outer surface comprises a first outer surface portion and a second outer surface portion with the first outer surface portion located radially outward of the second outer surface portion and a first chamfer extending from the first outer surface portion to the inlet end; and,a coating applied to the inner surface, where the coating comprises a bond coating and a ceramic top coating, at least a portion of the coating proximate the inlet end having a second chamfer opposed to the first chamfer and extending to the inlet end, the second chamfer thereby tapering a coating thickness towards the inlet end. 2. The combustion liner of claim 1, wherein a thickness of the first outer surface portion is greater than a thickness of the second outer surface portion. 3. The combustion liner of claim 1, wherein the first chamfer and the second chamfer form a reduced bluff body region at the inlet end. 4. The combustion liner of claim 3, wherein the bluff body at the inlet end provides for a recirculation zone proximate the inlet end of the combustion liner. 5. The combustion liner of claim 1, wherein the first chamfer has a chamfer angle from the first outer surface portion of the liner between approximately 5 degrees and 75 degrees to reduce risk of separation of airflow moving towards the inlet end. 6. The combustion liner of claim 1, wherein the coating applied to the inner surface of the combustion liner has a dense vertically cracked microstructure. 7. An inlet portion of a combustion liner comprising: a generally annular body having a first portion with a first liner thickness, a second portion with a second liner thickness different from the first liner thickness, and a third portion extending from the first portion to an inlet end of the combustion liner and having a thickness tapering at a first rate; and,a coating applied to an inner wall of the generally annular body, the inner wall being a surface of the combustion liner facing a combustion chamber, wherein at least a portion of the coating at the inlet end that is opposed to the third portion has a thickness that tapers at a second rate from a first coating thickness to a second coating thickness. 8. The inlet portion of claim 7, wherein the inlet end has a thickness of approximately 0.005-0.100 inches. 9. The inlet portion of claim 7, wherein the thickness of the combustion liner tapers at an angle of approximately 5-75 degrees relative to an outermost surface of the first portion. 10. The inlet portion of claim 7, wherein the thickness of the coating tapers at an angle of approximately 5-75 degrees relative to an inner surface of the coating at a location of the coating having the first coating thickness. 11. The inlet portion of claim 7, wherein the coating has a dense vertically cracked microstructure. 12. The inlet portion of claim 7, wherein the first coating thickness is approximately 0.010 inches to 0.200 inches. 13. A method of reducing a recirculation zone in a combustion liner comprising: providing a combustion liner having a first chamfer along an outer surface of the combustion liner extending to an inlet end of the combustion liner, providing a coating applied to an inner surface of the combustion liner, the inner surface being a surface of the combustion liner facing a combustion chamber, and providing a second chamfer to at least a portion of the coating on the inner surface that is opposed to the first chamfer and that extends to the inlet end of the combustion liner;directing a fuel and air mixture along the outer surface of the combustion liner;turning the fuel and air mixture about the inlet end of the combustion liner such that the mixture remains at least in close proximity to the chamfered portions of the combustion liner; and,directing the mixture into the combustion liner. 14. The method of claim 13, wherein the inlet end forms a bluff body having a reduced thickness compared to the remainder of the combustion liner and the coating. 15. The method of claim 14, wherein the bluff body has a thickness of approximately 0.005-0.050 inches. 16. A combustion liner comprising: a generally annular body having a thickness, an inlet end, and an opposing outlet end, the generally annular body having an inner surface facing a combustion chamber and an opposing outer surface, a portion of the outer surface contoured according to a first radius at the inlet end; anda coating applied to the inner surface, where the coating comprises a bond coating and a ceramic to coating, at least a portion of the coating at the inlet end that is opposed to the portion of the outer surface contoured according to the first radius contoured according to a second radius, such that the first radius blends into the second radius at the inlet end. 17. The combustion liner of claim 16, wherein the first radius is tangential to the second radius. 18. The combustion liner of claim 16, wherein the first radius is greater than the second radius. 19. The combustion liner of claim 16, wherein the second radius is greater than the first radius. 20. A combustion liner comprising: a generally annular body having thickness, an inlet end, and an opposing outlet end, the generally annular body having an inner surface facing a combustion chamber and an opposing outer surface, the outer surface having a contoured profile proximate the inlet end such that the outer surface comprises a first outer surface portion and a second outer surface portion with the first outer surface portion located radially outward of the second outer surface portion and a first chamfer extending from the first outer surface portion to the inlet end; and,a coating applied to the inner surface, where the coating comprises a bond coating and a ceramic top coating, at least a portion of the coating proximate the inlet end and opposed to the first chamfer having a radius at the inlet end. 21. A combustion liner comprising: a generally annular body having a thickness, an inlet end, and an opposing outlet end, the generally annular body having an inner surface facing a combustion chamber and an opposing outer surface, a portion of the outer surface contoured according to a radius at the inlet end; anda coating applied to the inner surface, where the coating comprises a bond coating and a ceramic top coating, at least a portion of the coating proximate the inlet end having a chamfer opposed to the portion of the outer surface contoured according to the radius and extending to the inlet end, the chamfer thereby tapering a coating thickness towards the inlet end.