Patent ID: 8133014

Claim:
An interstage seal assembly in a gas turbine engine comprising: a segmented fixed interstage seal support secured to a stationary inner shroud of a stator vane; a larger radial inward facing annular groove formed within the interstage seal support; an outer floating seal assembly secured within the larger radial inward facing annular groove such that radial displacement of the outer floating seal assembly can occur within the larger radial inward facing annular groove; the outer floating seal assembly forming a smaller radial inward facing annular groove; an inner floating seal assembly secured within the smaller radial inward facing annular groove such that radial displacement of the inner floating seal assembly can occur within the smaller radial inward facing annular groove; and, an annular compliant seal secured to the inner floating seal assembly to form a seal with a rotor disk of the gas turbine engine.