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A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform

A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform. Cooling underneath the radial seals may be done by conduction heath transfer through the platform of the shroud segments.

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1. 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 plat

1. 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. 2. The shroud defined in claim 1, wherein oppositely axially facing slots are respectively defined in said front and rear legs, the radially facing seals being received in said axially facing slots of the front and rear legs of circumferentially adjacent ones of said shroud segments. 3. The shroud defined in claim 2, wherein said oppositely axially facing slots are provided at a root portion of said front and rear legs at a junction of the front and rear legs with the radially outer back surface of the platform. 4. The shroud defined in claim 3, wherein said oppositely axially facing slots intersect respective radially extending front and rear slots respectively defined in said front and rear legs. 5. The shroud defined in claim 4, wherein said radially facing seals have a radial component extending into at least one of said front and rear slots. 6. The shroud defined in claim 1, wherein said platform is free of cooling holes underneath said radially facing seals. 7. The shroud defined in claim 1, wherein a plenum is defined between said front and rear legs, said radially facing seals being provided at a bottom of said plenum. 8. The shroud defined in claim 1, wherein the radially facing seals are laid flat in direct contact over a major surface area thereof against the radially outer back surface of the platform of the shroud segments. 9. A shroud segment of a circumferentially segmented shroud of a gas turbine engine, comprising a platform having a gaspath side and an opposed back side extending circumferentially between opposed first and second ends and opposed front and rear axially facing sides, axially spaced-apart front and rear legs extending radially from said back side of the platform, said front and rear legs defining with said back side of the platform a plenum for receiving cooling air, and oppositely axially facing slots defined in each circumferential end face of said front and rear legs at a junction region of the front and rear legs and the platform for holding a radially facing inter-segment seal in cooperation with an adjacent pair of slots of the front and rear legs of an adjacent shroud segment, and wherein the opposed first and second ends of the platform of the shroud segment are free of seal receiving slots between the front and rear legs, the radially facing inter-segment seal being spaced from the gas path side by a locally full thickness of the platform between the front and rear legs. 10. The shroud segment defined in claim 9, wherein said oppositely axially facing slots respectively intersect radially extending seal receiving slots defined in said front and rear legs. 11. The shroud segment defined in claim 9, wherein the platform is free of cooling holes in the inter-segment seal area of the platform. 12. A method for sealing and cooling circumferentially adjacent shroud segments in a gas turbine engine, each shroud segment being provided with a platform having a gas path side surface and an opposed back side surface, radially facing inter-segment seals being provided for sealing between adjacent shroud segments, the method comprising: a) locally maximizing the thickness of platform material underneath the radially facing inter-segment seals by mounting the radially facing inter-segment seals against the back side surface of the platform between each pair of adjacent shroud segments, each platform being free of seal receiving slots between opposed front and rear legs extending from the back side surface of the platform, the radially facing inter-segment seals being spaced from the gas path side surface by a locally full thickness of the platform between the front and rear legs; and b) cooling underneath the inter-segment seals by conduction heat transfer through the locally full thickness of the platform from the gas path side to the opposed back side of the platform. 13. The method defined in claim 12, wherein a) comprises inserting the inter-segment seal in axially facing slots defined in axially spaced-apart front and rear mounting legs extending radially from the back side of the platform of each shroud segment. 14. The method defined in claim 13, wherein the axially facing slots intersect radial slots defined in the front and rear legs, and wherein a) comprising engaging a radial component of the inter-segment seals in the radial slots to provide axial sealing as well as radial sealing.