COMBUSTOR COOLING STRUCTURE

摘要

The present invention relates to a transition member assembly (100) for a gas turbine. The transition member comprises one end part and another end part facing the end part. The transition member comprises: at least one outer liner (101); and at least one inner liner (102) forming a high temperature gas flow channel (103). A first section (200) of the transition member assembly positioned in an upstream of a first turbine stage (600) comprises a plurality of cooling openings (201). A cooling medium (202) accesses the inside of a plenum (203) and flows along at least the first section (200) of the transition member assembly.