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A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediat

A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

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1. A turbine engine cooling component for a gas turbine engine, which comprises:(a) a leading edge; (b) a trailing edge spaced from the leading edge; (c) a base connected to the trailing and leading edges and having a back surface and an arcuate inner surface; (d) a pair of spaced opposed axial side

1. A turbine engine cooling component for a gas turbine engine, which comprises:(a) a leading edge; (b) a trailing edge spaced from the leading edge; (c) a base connected to the trailing and leading edges and having a back surface and an arcuate inner surface; (d) a pair of spaced opposed axial side panels connected to the leading and trailing edges; (e) each of the side panels having a lower discourager spline seal slot extending longitudinally from the leading edge to the trailing edge of each side panel that is capable of receiving an edge of a discourager spline seal, each lower slot having at least a bottom wall and a top wall; (f) each of the side panels having an upper primary spline seal slot spaced above the lower slot and extending longitudinally from the leading edge to the trailing edge of each side panel, each upper slot having at least a bottom wall and a top wall, (g) a plurality of cooling air passages extending through the base from the back surface thereof and having spaced outlets exiting from at least one of the side panels between the bottom wall of the top slot and the bottom wall of the lower slot; (h) a plurality of spaced air flow pathways along the length of the lower slot and below the bottom wall of the upper slot that are capable of receiving air flowing over and above the discourager seal when positioned in the lower slot and passing the air flow around the edge and beneath the discourager seal.