Patent ID: 8740554

Claim:
An air seal assembly for a gas turbine engine comprising: a first rotor disk defined about an axis of rotation; a second rotor disk defined about said axis of rotation; a vane structure axially between said first rotor disk and said second rotor disk; a first cover plate including a first radially extending knife edge seal and a second radially extending knife edge seal defined about said axis of rotation, said first cover plate mountable to an aft surface of said first rotor disk for rotation therewith, said first radially extending knife edge seal and said second radially extending knife edge seal interfacing with said vane structure, and wherein said first radially extending knife edge seal defines a first diameter greater than a second diameter of said second radially extending knife edge seal; and a second cover plate with a radially extending knife edge seal defined about said axis of rotation, said second cover plate mountable to a forward surface of said second rotor disk for rotation therewith, said radially extending knife edge seal of the second cover plate interfacing with said vane structure.