Patent ID: 8651497

Claim:
A seal assembly for use in a cavity of a gas turbine engine, the cavity having a first wall, a second wall and a third wall, the seal assembly comprising: a first seal member having an undulating wear surface that contacts the first wall of the cavity at a first inner sealing surface and a first outer sealing surface, and the third wall of the cavity at a third sealing surface; a second seal member having an undulating wear surface that contacts the second wall of the cavity at a second inner sealing surface and a second outer sealing surface, and the third wall of the cavity at a fourth sealing surface; and a third seal member attached to the first seal member at a first joint located between the first inner sealing surface and the first outer sealing surface, and attached to the second seal member at a second joint located between the second inner sealing surface and the second outer sealing surface, such that the third seal member forms a resilient connection between the first seal member and the second seal member, wherein the first seal member and the second seal member are both thicker than the third seal member.