Outer rim seal assembly in a turbine engine

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;
• an annular seal member that extends axially from the vane assembly toward the blade assembly and includes a seal surface;
• and
• an annular wing member located radially inwardly from the hot gas path and the seal member and radially outwardly from the disc cavity, the wing member extending generally axially from an axially facing side of the blade assembly toward the vane assembly and including:
• a portion in close proximity to the seal surface of the seal member;
• and
• a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof, wherein outlets of the flow passages are located axially between a downstream axial end of the seal member and an upstream end of the platform wherein the flow passages each include a portion that is at least one of curved and angled in the circumferential direction against a direction of rotation of the turbine rotor as it extends radially outwardly through the wing member 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 by rotation of the turbine rotor and the blade assembly to limit hot gas ingestion from the hot gas path to the disc cavity by forcing the hot gas away from the seal assembly;
• and wherein the portion of each flow passage extends against the direction of rotation of the turbine rotor comprises a radially inner portion of the flow passage and each flow passage includes a middle portion including a direction shift such that the outlets of the cooling passages are angled with the direction of rotation of the turbine rotor.