Patent ID: 7857582

Claim:
A seal assembly for a turbine engine comprising a rotating rotor disk supporting blades, stationary vanes located adjacent to said blades, and an axially extending rotor arm supported on said rotor disk and located radially inwardly from said blades, the seal assembly comprising: a first seal member comprising a honeycomb structure supported on a radially inner end of said stationary vanes; a second seal member located on said rotor arm and comprising first and second seal surfaces wherein said second seal surface is radially spaced from said first seal surface, and said first and second seal surfaces are each substantially cylindrical surfaces, extending in the axial direction; said first seal member including a first seal portion located in facing relationship to said first seal surface to form a seal therebetween, and a second seal portion located in facing relationship to said second seal surface to form a seal therebetween; and said first seal portion comprising axially spaced upstream and downstream edges located radially inwardly from said second seal portion and defining a width in an axial direction of said turbine engine that is less than the width of said second seal portion in the axial direction.