Patent ID: 8388310

Claim:
A seal assembly for limiting gas leakage between a hot gas path and a disc cavity in a turbine engine comprising a plurality of stages, each stage comprising a plurality of stationary components connected by an annular inner shroud and a rotating disc supporting a plurality of blades, the seal assembly comprising: a wing member extending axially from a side of said disc toward a radial surface of said annular inner shroud, said wing member including an inner side and an outer side; a first wing flange extending radially outwardly from said outer side of said wing member toward an axial surface of said inner shroud; a first shroud flange extending radially inwardly from said axial surface of said inner shroud toward said outer side of said wing member to form, with said first wing flange, a labyrinth path between said hot gas path and said disc cavity; and a second shroud flange extending axially from said radial surface of said inner shroud toward said disc and being generally radially aligned with said wing member.