Patent ID: 8166764

Claim:
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; and a 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.