Patent ID: 7387488

Claim:
A shroud segment for a gas turbine engine, comprising: an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge; an outwardly-extending forward wall and an outwardly-extending aft wall; opposed first and second sidewalls, wherein said forward and aft walls and said sidewalls define an open shroud plenum; at least one leading edge cooling hole extending from said shroud plenum to said leading edge; and at least one sidewall cooling hole extending from said plenum to one of said sidewalls; wherein said flow path surface is free of cooling holes and a dense vertically microcracked thermal barrier coating is disposed on the flow path surface and not on the following: the outwardly-extending forward wall, the outwardly-extending aft wall, and the opposed first and second sidewalls.