Outer rim seal assembly in a turbine engine

A seal assembly 40 between a hot gas path (34) and a disc cavity (36) in a turbine engine includes a non-rotatable vane assembly (12A, 12B) including a row of vanes (14A, 14B) and an inner shroud (16A, 16B), a rotatable blade assembly adjacent to the vane assembly (18) and including a row of blades (20) and a turbine disc (22) that forms a part of a turbine rotor (24), and an annular wing member (42) located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages (44) extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.