Patent ID: 8684680

Claim:
A gas turbine engine shroud surrounding a rotor mounted for rotation about a central axis of a gas turbine engine, the shroud comprising a plurality of shroud segments disposed circumferentially one adjacent to another to form a full ring about the rotor, each of the shroud segments having a platform extending circumferentially between opposed first and second ends and opposed front and rear axially facing sides, the platform having a radially inner gas path surface and an opposed radially outer back surface, each of the shroud segments having axially spaced-apart front and rear legs extending radially outwardly from the radially outer back surface of the platform, and a plurality of radially facing seals provided between adjacent shroud segments, the circumferentially opposed first and second ends of the platform of the shroud segments being free of seal receiving slots between the front and rear legs, the radially facing seals being disposed radially outwardly of the platform of the shroud segments with a radially inner facing surface of the radial seals laying on the radially outer surface of adjacent platforms, the radially facing seals being spaced from the inner gas path surface by a locally full thickness of the platform between the front and rear legs, thereby providing for a continuous conduction heat transfer path underneath the radially facing seals through the platform from the radially inner gas path surface to the radially outer back surface.