Patent ID: 7762057
Filing Date: 2010-07-27
Classification: F02K

Abstract:
1. An aircraft comprising: at least one turbofan engine assembly having a fan driven by a core engine, a short nacelle around the fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle; a mixer duct shell substantially coaxial with and extending forwardly into the fan exhaust duct to provide a mixer duct between the mixer duct shell and the core engine; and a plurality of pillar mounts by which the mixer duct shell is mounted around the core engine, the pillar mounts positioned downstream of an outer wall exit plane of the fan exhaust duct and aligned to coincide with crowns of a plurality of lobes of a flow mixer on an aft section of the core engine within the mixer duct shell; the mixer duct shell comprising a leading edge rearward of a thrust reversal device of the at least one engine assembly, the shell leading edge configured with the thrust reversal device to provide, when the thrust reversal device is deployed, a gap between the leading edge and the thrust reversal device through which a flow of air from the fan exhaust duct is reversed into the mixer duct.