Patent ID: 8869507

Claim:
A nacelle assembly for a high-bypass gas turbine engine comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path, said fan nacelle includes a first fan nacelle section and a second fan nacelle section, said second fan nacelle section movable relative to said first fan nacelle section; and a cascade array including at least one section mechanically engaged with a cascade array actuator configured to translate said cascade array relative to said first fan nacelle section between a deployed position and a stored position, said second fan nacelle section being moveable in response to translation of said cascade array, said stored position locating said cascade array at least partially within said first fan nacelle section, wherein the interior of said second fan nacelle section is free of any section of said cascade array and said second fan nacelle section is spaced axially from said cascade array to define a clearance gap between said cascade array and said second fan nacelle section when said cascade array is located in said stored position.