Patent ID: 8016543

Claim:
A fan blade containment assembly for a gas turbine engine, comprising: a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region; and a first load spreader layer attached in contacting engagement with the fan case inner surface and located within the blade containing region; wherein in response to a blade-out event, the first load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event, and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade, and a first band layer mounted to the fan case outer surface in proximity to the blade containing region, wherein the first band layer is capable of carrying at least a portion of a hoop tensile load on the fan case that results from the blade-out event.