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A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that

A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis.

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What is claimed is: 1. A combustor liner comprising: a liner comprising an upstream end and a downstream end having a longitudinal axis extending therethrough; and a plurality of cooling holes formed in said liner, said cooling holes arranged along the longitudinal axis into a plurality of circumfe

What is claimed is: 1. A combustor liner comprising: a liner comprising an upstream end and a downstream end having a longitudinal axis extending therethrough; and a plurality of cooling holes formed in said liner, said cooling holes arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis; a first row of dilution holes; and a second row of dilution holes formed downstream from said first row of dilution holes, said plurality of cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows between said first and second rows of dilution holes and variably spaced apart along the longitudinal axis such that the spacing is at least one of gradually increasing and gradually decreasing from the first row of dilution holes downstream to the second row of dilution holes. 2. The combustor liner in accordance with claim 1, wherein said plurality of cooling holes each have the same diameter. 3. The combustor liner in accordance with claim 1, wherein said plurality of cooling holes are equidistantly spaced in a circumferential direction within a single row. 4. The combustor liner in accordance with claim 1, wherein said rows of cooling holes are arranged in at least one group, the axial spacing between adjacent rows gradually increasing in a downstream direction along the longitudinal axis. 5. The combustor liner in accordance with claim 1, wherein said plurality of cooling holes are axially slanted at an angle that is between approximately fifteen degrees and approximately twenty degrees. 6. The combustor liner in accordance with claim 1, wherein said plurality of cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis such that the spacing is gradually decreasing from the liner the upstream end at least partially towards the liner downstream end. 7. A gas turbine engine assembly comprising: a compressor; and a combustor coupled in flow communication with said compressor, said combustor comprising: at least one combustor liner having an upstream end and a downstream end having a longitudinal axis extending therethrough; a plurality of cooling holes formed in said liner, said cooling holes arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis; a first row of dilution holes; and a second row of dilution holes formed downstream from said first row of dilution holes, said plurality of cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows between said first and second rows of dilution holes and variably spaced apart along the longitudinal axis such that the spacing is at least one of gradually increasing and gradually decreasing from the first row of dilution holes downstream to the second row of dilution holes. 8. The gas turbine engine assembly in accordance with claim 7, wherein said plurality of cooling holes each have the same diameter. 9. The gas turbine engine assembly in accordance with claim 7, wherein said plurality of cooling holes are equidistantly spaced in a circumferential direction within a single row. 10. The gas turbine engine assembly in accordance with claim 7, wherein said plurality of rows of cooling holes are arranged in at least one group, the axial spacing between adjacent rows gradually increasing in a downstream direction along the longitudinal axis. 11. The gas turbine engine assembly in accordance with claim 7, wherein said cooling holes are axially slanted at an angle that is between approximately fifteen degrees and approximately twenty degrees. 12. The gas turbine engine assembly in accordance with claim 7, wherein said plurality of cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis such that the spacing is gradually decreasing from the liner upstream end at least partially towards the liner downstream end. 13. A method of fabricating a gas turbine engine combustor liner, said method comprising: providing a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough; and forming a plurality of cooling holes in the liner such that the plurality of holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis; forming a first row of dilution holes in the liner; and forming a second row of dilution holes downstream from the first row of dilution holes, the plurality of cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows between the first and second rows of dilution holes and variably spaced apart along the longitudinal axis such that the spacing is at least one of gradually increasing and gradually decreasing from the first row of dilution holes downstream to the second row of dilution holes. 14. The method in accordance with claim 13, further comprising forming the plurality holes such that the plurality of holes are equidistantly spaced in a circumferential direction and have the same diameter. 15. The method in accordance with claim 13, further comprising forming the plurality holes such that the plurality of holes are axially slanted at an angle that is between approximately fifteen degrees and approximately twenty degrees. 16. The method in accordance with claim 13, further comprising forming the plurality of holes such that the spacing between adjacent rows is gradually decreasing from the liner upstream end at least partially towards the liner downstream end.