Patent ID: 8834105
Filing Date: 2014-09-16
Classification: F01D,F05D

Abstract:
1. A turbine shroud apparatus for a gas turbine engine having a central axis, comprising: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; a turbine vane disposed upstream of the shroud segment and arranged such that there is a continuous mechanical load path from the turbine vane to the forward wall of the shroud segment; an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure, and wherein the stationary structure includes at least one axially-facing bearing surface which is in direct contact with the aft wall of the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure, the load spreader comprising: wherein the shroud segment is disposed so as to absorb at least one axially-aligned force from the turbine vane and transfer the axially-aligned force to the bearing surface.