Patent ID: 7721525
Filing Date: 2010-05-25
Classification: B64D,F01D,F02C,F02K,F05D,Y02T,Y10T

Abstract:
1. An inlet assembly for a turbofan engine nacelle, the inlet assembly having an aft end configured for attachment to a forward end of a fan housing and comprising: an inner barrel; an outer barrel disposed around said inner barrel; and a rear support extending between aft portions of the inner barrel and the outer barrel and supporting the outer barrel relative to the inner barrel, said rear support comprising at least one plate extending between said inner barrel and said outer barrel and enclosing the aft end of the inlet assembly, said plate having at least one energy absorber and a plurality of circumferentially spaced ribs formed in said plate, the ribs extending radially outward from the energy absorber, said energy absorber defining a zone of deformation adjacent said inner barrel, the zone of deformation being deformable in response to an applied force during a blade-out event without substantial deformation of portions of the plate that include the spaced ribs.