Patent ID: 9260979
Filing Date: 2016-02-16
CPC Classification: F01D,F05D

Claim Text:
1. A seal assembly between a hot gas path and a disc cavity in a turbine engine comprising: a non-rotatable vane assembly including a row of vanes and an inner shroud; a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, the blades extending from a platform of the blade assembly; and an annular wing member located radially between the hot gas path and the disc cavity and extending generally axially from the blade assembly toward the vane assembly, the wing member including a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof, wherein the flow passages each include a portion that is curved against the direction of rotation of the turbine rotor as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path during operation of the engine.