Gas turbine combustion apparatus.

摘要

A gas turbine cooling apparatus is disclosed in which a flow sleeve (6) is provided to surround a combustor liner (3) and a tail pipe (5) substantially over their full length. A group of small holes (11) for impinge-cooling an outer wall of the tail pipe (5) are formed in a region of the flow sleeve close to a turbine. Further, opening portion for introducing cooling air are provided closer to the combustor liner than the small holes (11). Thus, the outer wall of the tail pipe (5) and the wall of the combustor liner (3) are cooled by the cooling air flowing between the tail pipe (5), the combustor liner (3) and the flow sleeve (6).