Aircraft engine nacelle with translating inlet cowl

摘要

A nacelle (120) for a turbofan aircraft engine (100) having a fan case (116) with a fan case forward edge includes an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge (127b). The inner barrel aft edge (127b) is configured to be affixed to the fan case forward edge in a stationary position on the engine. The nacelle (120) also includes a translating inlet cowl (124) having an inlet lip (128) with an aft inlet lip edge and an outer skin (129) with rear edge (124b). The translating inlet cowl (124) is configured to be movably attached to one or more stationary portions of the engine such that the inlet cowl (124) is selectively movable between a stowed flight position and an extended service position.