TURBINE SHROUD COOLING ASSEMBLY FOR GAS TURBINE SYSTEM

摘要

PROBLEM TO BE SOLVED: To provide a turbine shroud cooling assembly for a gas turbine system.SOLUTION: A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path. The assembly also includes at least one rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through a main passage of the rib for cooling the inner shroud component.