Patent ID: 8784041

Claim:
A turbine shroud segment for a turbine shroud of a gas turbine engine, the segment comprising a metal injection molded (MIM) shroud body, the MIM shroud body 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 first and second lateral sides, said MIM shroud body including a platform having a hot gas path side surface and a back side surface, and forward and aft arms extending from the back side surface of the platform, said forward and aft arms being axially spaced-apart from each other, a seal groove defined in the first lateral side of the MIM shroud body; and a feather seal projecting integrally from the second lateral side of the MIM shroud body for engagement in the seal groove of a similar circumferentially adjacent turbine shroud segment, the feather seal being made from a different material than said MIM shroud body and having a proximal end imbedded in said second lateral side of said MIM shroud body.