Coolable blade tip shroud

Claim 1

A shroud, which surrounds a portion of the flow path for the working medium gases in the turbine section of a gas turbine engine, comprising: a plurality of arcuate segments disposed in end to end relationship wherein each arcuate segment has a plurality of lugs which interlock with corresponding lugs from the adjacent segment and wherein each pair of adjacent segments forms therebetween a substantially triangular shaped groove, the segments forming a sealing surface, having a multiplicity of cooling holes disposed therein, and including a plurality of axially adjacent chambers which extend circumferentially beneath the sealing surface; a sealing member disposed within each of said triangular shaped grooves to inhibit the flow of fluid medium between the adjacent segments; and baffle means, including a plurality of orifices incorporated therein, which is disposed across one side of each chamber of the arcuate segments, wherein the cooling holes of the sealing surface and orifices of the baffle means are sized and spaced to provide a substantially uniform pressure ratio across the sealing surface during operation of the engine.