SYMPOSIA PAPER Published: 01 January 1975
STP33158S

Studies on the Impact Structural Damage of Composite Blades

Source

The dynamic response of jet engine fan blades subjected to foreign object impact loadings has been investigated. Two analytical methods based upon a discrete mass distribution have been used for model purposes. Numerical results for blade natural frequencies, tip displacements, and bending moments have been obtained for boron-aluminum, graphite-epoxy, titanium, and stainless steel blades. Numerical data have been discussed for the various materials considered.

Author Information

Sun, CT
National Research Council, Air Force Materials Laboratory, Wright-Patterson Air Force Base, Dayton, Ohio
Sierakowski, RL
National Research Council, Air Force Materials Laboratory, Wright-Patterson Air Force Base, Dayton, Ohio
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Details
Developed by Committee: D30
Pages: 212–227
DOI: 10.1520/STP33158S
ISBN-EB: 978-0-8031-4651-8
ISBN-13: 978-0-8031-0357-3