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Fatigue Crack Growth Behaviour of Aa6013 Aluminum Alloy
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The effect of different aging treatments on fatigue crack growth behavior ofAA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimenswere prepared in L-T and T-L direction for fatigue crack growth tests. Sampleswere in T651 as received, T42 which is solution heat treated at 538 şC for 90minutes, water quenched and aged in room temperature for 96 hours, and onegroup of samples were overaged at 245 şC for 12 hours after T42 condition wasachieved. Hardness and conductivity measurements were achieved for allconditions after the heat treatments.Fatigue crack growth tests were performed at as received condition T651, T42and 245 şC aged samples in laboratory air with sinusoidal loading of stress ratioR=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance isobserved for T651 T-L and 245 şC overaged L-T condition.
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