COOLING A TURBINE SHROUD SEGMENT ABND REUSING THE COOLING AIR
摘要
A cooled turbine shroud segment (12) for a gas turbine engine, having an axially extending shroud ring segment (18) with an inner surface (19), an outer surface (20) an upstream flange (21) and a downstream flange (22) . The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate (23) is disposed on the outer surface of the shroud ring between the upstream flange (21) and the downstream flange (22) with an impingement plenum (24) defined between the impingement plate (23) and the outer surface (20) . Axially extending cooling bores (25) in the ring segment extend between the impingement plenum (24) and an outlet. A trough (27) adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.