Patent ID: 9140135
Filing Date: 2015-09-22
Classification: B29C,B29L,F01D,F02K,F05D,F16B

Abstract:
1. A gas turbine engine fan section comprising: a plurality of composite layers defining a generally cylindrical case; an attachment flange extending radially outward from the cylindrical case, the attachment flange comprising a portion of the plurality of composite layers that define the cylindrical case forming a continuous radius turned radially outward transverse to a portion of the same plurality of composite layers defining the cylindrical case; a metallic backing secured to the attachment flange, wherein the attachment flange includes a radius on the outer surface of the cylindrical case and the metallic backing includes a corresponding radius; at least one fastener securing the metallic backing to the attachment flange, wherein a terminating end of each fastener does not extend upstream beyond the attachment flange; a corrosion barrier disposed between the metallic backing and the attachment flange with the metallic backing adhered to the corrosion barrier with an adhesive; and a fan section including a plurality of fan blades disposed within the generally cylindrical case.