Patent ID: 8784044
Filing Date: 2014-07-22
Classification: B22F,F01D,F05D,Y10T

Abstract:
1. A turbine shroud segment for a turbine shroud of a gas turbine engine, the segment comprising a metal injection molded (MIM) shroud body, said MIM shroud body including a platform having a hot gas path side surface and a back side surface, the platform being axially defined from a leading edge to a trailing edge in a direction from an upstream position to a downstream position of a hot gas flow passing through the turbine shroud, and being circumferentially defined between opposite lateral sides of the platform, and forward and aft hooks extending from the back side surface of the platform, said forward and aft hooks being axially spaced-apart from each other; and a core imbedded in the MIM shroud body, said core having a platform reinforcing section extending longitudinally along a circumferential direction of the platform between said hot gas path and back side surfaces.