Patent ID: 7959106

Claim:
An integrated propulsive system for an aircraft, comprising: a turbofan engine, including an intermediate casing; and a nacelle which bears the intermediate casing of the turbofan engine which defines an annular flow space for a secondary stream around the turbofan engine, the nacelle comprises a downstream cylindrical structure which includes a fixed framework which is fastened via engine attachment elements to a part of the aircraft and which is fastened to the intermediate casing of the turbofan engine, and a moveable part which is borne by the fixed framework and which moves between a closed position during operation of the turbofan engine and an open position in which the movable part is moved to allow access to engine components, wherein the system includes a locking device which secures the moveable part to the fixed framework in the closed position, wherein the fixed framework includes a downstream annular part in the shape of an annulus and the secondary stream travels through the downstream annular part, and wherein the fixed framework includes an upstream annular flange which is fastened to an external annular flange of the intermediate casing of the turbofan engine.