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FOD impact testing of composite fan bladesThe results of impact tests on large, fiber composite fan blades for aircraft turbofan engine applications are discussed. Solid composite blades of two different sizes and designs were tested. Both graphite/epoxy and boron/epoxy were evaluated. In addition, a spar-shell blade design was tested that had a boron/epoxy shell bonded to a titanium spar. All blades were tested one at a time in a rotating arm rig to simulate engine operating conditions. Impacting media included small gravel, two inch diameter ice balls, gelatin and RTV foam-simulated birds, as well as starlings and pigeons. The results showed little difference in performance between the graphite and boron/epoxy blades. The results also indicate that composite blades may be able to tolerate ice ball and small bird impacts but need improvement to tolerate birds in the small duck and larger category.
Document ID
19740015228
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johns, R. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-71544
Meeting Information
Meeting: Natl. SAMPE Symp. and Exhibition
Location: Buena Park, CA
Country: United States
Start Date: April 23, 1974
End Date: April 25, 1974
Accession Number
74N23341
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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