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Impact resistance of fiber composite blades used in aircraft turbine enginesResistance of advanced fiber reinforced epoxy matrix composite materials to ballistic impact was investigated as a function of impacting projectile characteristics, and composite material properties. Ballistic impact damage due to normal impacts, was classified as transverse (stress wave delamination and splitting), penetrative, or structural (gross failure). Steel projectiles were found to be gelatin ice projectiles in causing penetrative damage leading to reduced tensile strength. Gelatin and ice projectiles caused either transverse or structural damage, depending upon projectile mass and velocity. Improved composite transverse tensile strength, use of dispersed ply lay-ups, and inclusion of PRD-49-1 or S-glass fibers correlated with improved resistance of composite materials to transverse damage. In non-normal impacts against simulated blade shapes, the normal velocity component of the impact was used to correlate damage results with normal impact results. Stiffening the leading edge of simulated blade specimens led to reduced ballistic damage, while addition of a metallic leading edge provided nearly complete protection against 0.64 cm diameter steel, and 1.27 cm diameter ice and gelatin projectiles, and partial protection against 2.54 cm diameter projectiles of ice and gelatin.
Document ID
19740002613
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Friedrich, L. A. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Preston, J. L., Jr. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
PWA-4727
NASA-CR-134502
Accession Number
74N10726
Funding Number(s)
CONTRACT_GRANT: NAS3-15568
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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