Patent ID: 8677759

Claim:
A gas turbine combustor comprising: a combustor liner having a forward end and an aft end; a flow sleeve surrounding said combustor liner, said flow sleeve also having forward and aft ends substantially radially adjacent the forward and aft ends, respectively, of said combustor liner, the aft end of the combustor liner connected to a transition piece adapted to supply hot combustion gases to a turbine, the aft end of the flow sleeve supporting an external annular ring welded to or integral with said flow sleeve and formed with plurality of outward projecting bosses; a plurality of cooling bores extending substantially radially through said bosses, said annular ring and said flow sleeve, opening into an annular space radially between the flow sleeve and the combustor liner, at least some of said plurality of cooling bores formed at an acute angle relative to a longitudinal axis of said combustor liner to thereby direct cooling air in a substantially radial direction to a target area on said combustor liner.