Patent ID: 8844861
Filing Date: 2014-09-30
Classification: B64D,Y02T

Abstract:
1. An aircraft propulsion system comprising: a bypass turbojet engine surrounded by a nacelle defining an annular flow space for a secondary stream; and means for attaching the engine to a pylon for fastening to a structural element of an aircraft, wherein a downstream portion of the nacelle comprises an inner structure forming a body of revolution that surrounds an annular wall defining an outer boundary of an annular flow space for a primary stream, that extends axially between an annular intermediate casing of the engine and an annular exhaust casing of the engine defining an outer boundary of an outlet of the primary stream, and that defines an inside of a flow section for the secondary stream around a body of the engine, wherein the inner structure of the downstream portion of the nacelle comprises a rigid framework including an upstream annular frame fastened by bolting to the intermediate casing of the engine, a downstream annular frame that surrounds the exhaust casing of the engine and that includes support means for supporting the exhaust casing of the engine, and longitudinal arms connecting the upstream and downstream frames together, and wherein the annular downstream frame of the inner structure is fastened to the pylon by flexible or hinged suspension means.