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A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring

A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.

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1. A combustor assembly for a turbine engine, the combustor assembly comprising: a combustor liner;a flow sleeve surrounding the combustor liner;a first annulus defined radially between the combustor liner and the flow sleeve;a plurality of rows of cooling holes formed in the flow sleeve;a plenum ri

1. A combustor assembly for a turbine engine, the combustor assembly comprising: a combustor liner;a flow sleeve surrounding the combustor liner;a first annulus defined radially between the combustor liner and the flow sleeve;a plurality of rows of cooling holes formed in the flow sleeve;a plenum ring radially surrounding the combustor liner in the first annulus, the plenum ring comprising a plurality of axial flow passages for directing axial air flow and a plurality of radial flow passages for directing radial air flow;a transition duct connected to the combustor liner;an impingement sleeve connected to the flow sleeve and radially surrounding the transition duct; anda second flow annulus defined radially between the transition duct and the impingement sleeve, wherein the plenum ring is positioned in the first flow annulus adjacent to the transition duct so that the axial flow passages direct air from the second flow annulus to the first flow annulus, and the radial flow passages direct radial air onto the combustor liner. 2. The combustor assembly of claim 1, wherein the plenum ring has an inner ring, the inner ring having an upstream portion adjacent to the impingement sleeve and a downstream portion opposite the upstream portion, and wherein a distance between the downstream portion and the combustor liner is less than a distance between the upstream portion and the combustor liner. 3. The combustor assembly of claim 1, and further comprising a first flow hole formed in each radial flow passage, wherein the first flow holes are aligned with a first row of cooling holes in the flow sleeve. 4. The combustor assembly of claim 3, wherein the first flow hole has a smaller diameter than the cooling hole with which it is aligned. 5. The combustor assembly of claim 3, and further comprising a second flow hole formed in each radial flow passage, wherein the second flow holes are aligned with a second row of cooling holes in the flow sleeve. 6. The combustor assembly of claim 1, and further comprising axial flow blockers attached to each radial flow passage so that axial air cannot enter radial flow passages. 7. The combustor assembly of claim 1, wherein the first row of cooling holes is immediately adjacent to the impingement sleeve. 8. The combustor assembly of claim 7, wherein the first flow hole has a smaller diameter than the second flow hole. 9. The combustor assembly of claim 8, wherein the first hole is closer to the combustor liner than the second flow hole. 10. The combustor assembly of claim 1, wherein the first flow hole is closer to the combustor liner than the second flow hole. 11. The combustor assembly of claim 1, wherein the plenum ring further comprises: an upstream flange and a downstream flange axially spaced apart; anda first flow hole formed in each radial passage so that air radially flows through each radial passage,wherein the plurality of axial passages axially extend between the upstream flange and the downstream flange, each axial passage having an axial bypass channel so that air flows through the bypass channel in an axial direction, and wherein the plurality of radial passages axially extend between the upstream flange and the downstream flange, each radial passage having an upstream section with a first depth and a downstream section with a second depth different from the first depth. 12. The combustor assembly of claim 11, wherein the plenum ring further comprises a second flow hole formed in each radial passage. 13. The combustor assembly of claim 12, wherein the first flow hole has a larger diameter than the second flow hole. 14. The combustor assembly of claim 12, wherein the first depth is deeper than the second depth, and wherein the first flow hole is formed in the upstream section and the second flow hole is formed in the downstream section. 15. The combustor assembly of claim 1, wherein the plenum ring has an inner ring, the inner ring having an upstream portion adjacent to the impingement sleeve and a downstream portion opposite the upstream portion, and wherein a distance between the downstream portion and the combustor liner is greater than a distance between the upstream portion and the combustor liner. 16. A method of cooling a combustor liner, the method comprising: surrounding a combustor liner with the flow sleeve, so that a first flow annulus is formed therebetween, wherein the flow sleeve includes a first row of cooling holes and a second row of cooling holes;radially surrounding the combustor liner with a plenum ring having a plurality of axial flow passages and a plurality of radial flow passages, wherein each radial flow passage comprises: a first flow hole aligned with the first row of cooling holes so that air flows into the first flow annulus and impinges on the combustor liner; anda second flow hole aligned with the second row of cooling holes so that air radially flows through the radial flow passage and impinges upon the combustor liner;directing axial air flow through the axial flow passages; anddirecting radial air flow through the radial flow passages. 17. The method of claim 16, and further comprising: locating an axial flow blocker at each radial flow passage so that axial air flow cannot enter the radial flow passage. 18. The method of claim 16, wherein the first flow holes are closer to the combustor liner than the second flow holes. 19. The method of claim 16, wherein first flow holes have a smaller diameter than the second flow holes.