Patent ID: 8529188

Claim:
A gas turbine engine comprising: a core engine driving a fan; a fan nacelle surrounding the fan and providing an inner surface facing the fan, the fan nacelle including an inlet lip adjoining the inner surface; and a ring arranged at the inner surface axially upstream from the fan, the ring having a deployed position in which the ring is spaced radially inwardly from the inner surface to provide a gap there between through which air flows, and a stowed position in which the ring is arranged radially outwardly from the deployed position and proximate to the inner surface, wherein the ring includes circumferentially arranged ring segments, the ring segments interleaved with one another at adjacent end portions with the end portions circumferentially overlapping one another, wherein the ring segments are interleaved with one another such that the ring segments overlap one another in both the deployed position and the stowed position, and wherein the entirety of each of the ring segments is spaced radially inward from the inner surface when the ring is in the deployed position.