Interstage seal for a gas turbine engine and corresponding assembly method

摘要

An air seal assembly for a gas turbine engine includes a first cover plate (58) with a radially extending knife edge seal (88A) defined about and axis of rotation. The first cover plate (58) is mountable to a first rotor disk (56) for rotation therewith. The first radially extending knife edge seal (88A) interfaces with a vane structure (72). A second cover plate (60) with a second radially extending knife edge seal (90A) defined about the axis of rotation, is mountable to a second rotor disk (62) for rotation therewith. The second radially extending knife edge seal (90A) also interfaces with the vane structure (72).