Composite case armor for jet engine fan case containment
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United States of America Patent
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Sep 13, 2011
Grant Date -
Mar 12, 2009
app pub date -
Apr 2, 2007
filing date -
Apr 2, 2007
priority date (Note) -
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Abstract
A gas turbine fan blade containment assembly includes a fan case having an inner surface surrounding a jet engine fan and an outer surface. Mounted on the inner surface and across a blade containing region of the fan case is a load spreader layer for initially receiving a point load from a fan blade release (a “blade-out event”). A band layer is mounted to an outer surface of the fan case for carrying at least a portion of a hoop tensile load on the fan case resulting from the blade-out event, and separator film layer is mounted between the outer surface of the fan case and the band layer to retard the formation of stress concentrations in the band layer. In one embodiment, the load spreader layer includes a plurality of circumferentially-arrayed load spreader layer segments.
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