Patent ID: 8864451

Claim:
An interstage seal for installation between forward and aft stage discs of a turbine section of a gas turbine engine, the seal comprising: a forward annular portion which extends forward to contribute to an air seal at the outer periphery of the forward stage disc, an aft annular portion which extends rearward to contribute to an air seal at the outer periphery of the aft stage disc, and a peripheral slot into which static vane inner rails are loadable; wherein the seal comprises a first component which provides the forward annular portion, and a second component which provides the aft annular portion and is separably connectable to the first component such that the first and second components, when connected, cooperate to form the peripheral slot and loading the static vane inner rails into the slot prevents the second component from separating from the first component, and wherein one of the first component or the second component has a male mating feature and the other of the first component or the second component has a female mating feature, and when the first and second components are connected the mating features interengage to prevent relative movement of the first and second components, wherein the second component, on connection with the first component, is slidable axially rearwardly relative to the first component to interengage the mating features of the first and second components and form the peripheral slot.