Patent ID: 9127549
Filing Date: 2015-09-08
Classification: F01D,F05D

Abstract:
1. A turbine shroud cooling assembly for a gas turbine system comprising: an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream; an inner shroud component disposed radially inward of, and directly bonded to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway; and a cover disposed proximate an inner surface of the inner shroud component, the cover enclosing and sealing the plurality of microchannels from a hot gas path of the gas turbine system, the cover directly defining a radially inner end of the plurality of microchannels, wherein the cover includes a layer proximate the plurality of microchannels comprising a thermal barrier coating having a thickness ranging from 0.4 mm to 1.5 mm.