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A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are

A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.

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1. A combustor for a turbine engine, comprising: a combustor liner;an end cap mounted at an upstream end of the combustor liner; anda flow sleeve that surrounds an exterior of the combustor liner, wherein compressed air flows through an annular space between an outer surface of the combustor liner a

1. A combustor for a turbine engine, comprising: a combustor liner;an end cap mounted at an upstream end of the combustor liner; anda flow sleeve that surrounds an exterior of the combustor liner, wherein compressed air flows through an annular space between an outer surface of the combustor liner and an inner surface of the flow sleeve, wherein cooling holes penetrate the flow sleeve, the cooling holes allowing compressed air to flow from an exterior of the flow sleeve into the annular space, and wherein the flow sleeve includes at least one reduced diameter portion, a height of the annular space being smaller along the at least one reduced diameter portion of the flow sleeve than along other portions of the flow sleeve, wherein a diameter of the cooling holes along the at least one reduced diameter portion of the flow sleeve is greater than a diameter of the cooling holes along the other portions of the flow sleeve. 2. The combustor of claim 1, wherein a greater number of cooling holes per unit area are formed along the at least one reduced diameter portion of the flow sleeve than along other portions of the flow sleeve. 3. The combustor of claim 2, wherein cooling thimbles are mounted in the cooling holes located along the at least one reduced diameter portion of the flow sleeve. 4. The combustor of claim 3, wherein each of the cooling thimbles includes a cylindrical barrel that extends from the inner surface of the flow sleeve towards the outer surface of the combustor liner. 5. The combustor of claim 1, wherein the at least one reduced diameter portion comprises: a first reduced diameter portion;a second reduced diameter portion; andan intermediate portion that is located between the first and second reduced diameter portions, wherein a height of the annular space along the intermediate portion is greater than a height of the annular space along the first and second reduced diameter portions. 6. The combustor of claim 5, wherein a height of the annular space is smaller along the first reduced diameter portion of the flow sleeve than along the second reduced diameter portion of the flow sleeve. 7. The combustor of claim 5, wherein the first reduced diameter portion of the flow sleeve is located at an upstream end of the combustor adjacent a combustion zone inside the combustor liner. 8. The combustor of claim 7, wherein the second reduced diameter portion of the flow sleeve is located at a downstream end of the combustor adjacent a transition duct. 9. The combustor of claim 5, wherein a greater number of cooling holes per unit area are formed along the first reduced diameter portion of the flow sleeve than along the second reduced diameter portion of the flow sleeve. 10. A combustor for a turbine engine, comprising: a combustor liner;an end cap mounted at an upstream end of the combustor liner; anda flow sleeve that surrounds an exterior of the combustor liner, wherein compressed air flows through an annular space between an outer surface of the combustor liner and an inner surface of the flow sleeve in a direction that is opposite to a flow direction of combustion gases inside the combustor liner, wherein cooling holes penetrate the flow sleeve, the cooling holes allowing compressed air to flow from an exterior of the flow sleeve into the annular space, wherein the flow sleeve includes a reduced diameter portion where a height of the annular space between the inner surface of the flow sleeve and the outer surface of the combustor is smaller than along other portions of the combustor liner, the reduced diameter portion surrounding a combustion zone for a secondary fuel nozzle of the combustor, and wherein a diameter of the cooling holes along the reduced diameter portion of the flow sleeve is greater than a diameter of the cooling holes along the other portions of the flow sleeve. 11. The combustor of claim 10, wherein there is a greater number of cooling holes per unit area along portions of the flow sleeve that are adjacent smaller height portions of the annular space as compared to those portions of the flow sleeve that are adjacent greater height portions of the annular space. 12. The combustor of claim 10, further comprising cooling thimbles that are mounted in the cooling holes located along the portion of the flow sleeve that surrounds the combustion zone for a secondary fuel nozzle of the combustor. 13. The combustor of claim 10, wherein the reduced diameter portion of the flow sleeve comprises a first reduced diameter portion, and wherein the flow sleeve also includes a second reduced diameter portion and an intermediate portion that is located between the first and second reduced diameter portions, wherein a height of the annular space along the intermediate portion is greater than a height of the annular space along the first and second reduced diameter portions. 14. The combustor of claim 13, wherein the height of the annular space along the first reduced diameter portion of the flow sleeve is smaller than the height of the annular space along the second reduced diameter portion of the flow sleeve.