Turbine shroud segment cooling system and method

摘要

The present embodiments are generally directed toward systems and methods for cooling one or more shroud segments (52) of a gas turbine engine. For example, in a first embodiment, a shroud segment (52) is provided that is configured to at least partially surround a turbine blade of a turbine engine. The shroud segment (52) includes a body (60) and a microchannel (72,78) disposed in the body. The microchannel is configured to flow a cooling fluid through the body.