Methods and systems for cooling integral turbine shroud assemblies

摘要

A turbine shroud assembly (110) for a gas turbine engine is provided. The turbine shroud assembly includes a shroud segment (130) including a leading edge (133), a trailing edge (137) and a midsection defined therebetween, a shroud support (144) circumferentially spanning and supporting the shroud segment, the shroud support including a forward section (146), a midsection (148) and an aft section (150), an annular shroud ring structure (158) configured to support the shroud support, a first active convection cooling zone (173) defined between the shroud segment and the shroud support at least one feed hole (174) extending through the shroud support and configured to meter a first portion (171) of cooling air (170) into the first active convection cooling zone, and a first inactive convection cooling zone (211) defined between the shroud support and the annular shroud ring structure.