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The effect of different aging treatments on fatigue
crack growth behavior of
AA6013 aluminum alloy was investigated. C(T)
(Compact Tension) specimens
were prepared in L-T and T-L direction for fatigue
crack growth tests. Samples
were in T651 as received, T42 which is solution heat
treated at 538 ºC for 90
minutes, water quenched and aged in room temperature
for 96 hours, and one
group of samples were overaged at 245 ºC for 12
hours after T42 condition was
achieved. Hardness and conductivity measurements
were achieved for all
conditions after the heat treatments.
Fatigue crack growth tests were performed at as
received condition T651, T42
and 245 ºC aged samples in laboratory air with
sinusoidal loading of stress ratio
R=0.1 and at a frequency of 1 Hz. The highest
fatigue crack growth resistance is
observed for T651 T-L and 245 ºC overaged L-T
condition.
crack growth behavior of
AA6013 aluminum alloy was investigated. C(T)
(Compact Tension) specimens
were prepared in L-T and T-L direction for fatigue
crack growth tests. Samples
were in T651 as received, T42 which is solution heat
treated at 538 ºC for 90
minutes, water quenched and aged in room temperature
for 96 hours, and one
group of samples were overaged at 245 ºC for 12
hours after T42 condition was
achieved. Hardness and conductivity measurements
were achieved for all
conditions after the heat treatments.
Fatigue crack growth tests were performed at as
received condition T651, T42
and 245 ºC aged samples in laboratory air with
sinusoidal loading of stress ratio
R=0.1 and at a frequency of 1 Hz. The highest
fatigue crack growth resistance is
observed for T651 T-L and 245 ºC overaged L-T
condition.