Patent ID: 6340135
Filing Date: 2002-01-22
Classification: B64D

Abstract:
An aircraft propulsion system arrangement to determinably reduce or eliminate inlet cowl induced bending of an aircraft jet engine case during certain flight conditions, which arrangement comprises a turbofan aircraft jet engine having an engine case with a fan case portion, a nacelle structure housing the engine and having a forward generally cylindrical nacelle portion and a rearward nacelle portion, and a pylon structure to support the engine and the nacelle structure while permitting relative movement between the forward and rearward nacelle portions, wherein the pylon structure supports the forward nacelle portion independently of its support of the engine while permitting translational movement of the forward nacelle portion forwardly on the pylon structure from a locked operational position during operation of the engine to a forward servicing position during non-operation of the engine, wherein the forward nacelle portion provides an air inlet cowl portion directly coupled to said fan case portion of the engine for the supply of air to the engine and to an integral fan housing portion which surrounds the fan case portion of the engine, wherein the forward nacelle portion includes a noselip portion having an inner main skin which extends rearwardly to sealingly engage said fan case portion of the engine, and an outer generally concentric main skin which extends rearwardly to lockingly engage the rearward nacelle portion, and in the forward servicing position of the forward nacelle portion, it may be spaced forwardly from said fan case portion of the engine to uncover the outer fan case portion of the engine to give access thereto and to components mounted thereon which are inaccessible when the forward nacelle portion is secured in the operational position.