Abstract
The mechanical and constant fatigue behavior of AA6063-T6 exposed to aggressive 3.5 wt.% NaCl solution corrosion
has been investigated. The selected alloy used in this work is typically employed in structured components like aircraft
spars. Some tensile and fatigue specimens were hardened using shot peening (SP) treatment for 10 mins, shot peening
time. The experimental results revealed that the (UTS) and (YS) were reduced by 10.88% and 9% respectively due to
corrosion while ductility increased from 12.5% to 14%. SP treatment improved the above reduction percentage to 8.17%
for (UTS) and 7.53% for (YS). Corrosion-fatigue had a significant impact on fatigue life as well as strength at lower
stress levels, but had no influence at higher stress levels. The endurance fatigue limit (EFL) reduced to 62.64 MPa and
raised to 64 MPa due to corrosion when using (SP) treatment.The mechanical and constant fatigue behavior of AA6063-T6 exposed to aggressive 3.5 wt.% NaCl solution corrosion
has been investigated. The selected alloy used in this work is typically employed in structured components like aircraft
spars. Some tensile and fatigue specimens were hardened using shot peening (SP) treatment for 10 mins, shot peening
time. The experimental results revealed that the (UTS) and (YS) were reduced by 10.88% and 9% respectively due to
corrosion while ductility increased from 12.5% to 14%. SP treatment improved the above reduction percentage to 8.17%
for (UTS) and 7.53% for (YS). Corrosion-fatigue had a significant impact on fatigue life as well as strength at lower
stress levels, but had no influence at higher stress levels. The endurance fatigue limit (EFL) reduced to 62.64 MPa and
raised to 64 MPa due to corrosion when using (SP) treatment.
has been investigated. The selected alloy used in this work is typically employed in structured components like aircraft
spars. Some tensile and fatigue specimens were hardened using shot peening (SP) treatment for 10 mins, shot peening
time. The experimental results revealed that the (UTS) and (YS) were reduced by 10.88% and 9% respectively due to
corrosion while ductility increased from 12.5% to 14%. SP treatment improved the above reduction percentage to 8.17%
for (UTS) and 7.53% for (YS). Corrosion-fatigue had a significant impact on fatigue life as well as strength at lower
stress levels, but had no influence at higher stress levels. The endurance fatigue limit (EFL) reduced to 62.64 MPa and
raised to 64 MPa due to corrosion when using (SP) treatment.The mechanical and constant fatigue behavior of AA6063-T6 exposed to aggressive 3.5 wt.% NaCl solution corrosion
has been investigated. The selected alloy used in this work is typically employed in structured components like aircraft
spars. Some tensile and fatigue specimens were hardened using shot peening (SP) treatment for 10 mins, shot peening
time. The experimental results revealed that the (UTS) and (YS) were reduced by 10.88% and 9% respectively due to
corrosion while ductility increased from 12.5% to 14%. SP treatment improved the above reduction percentage to 8.17%
for (UTS) and 7.53% for (YS). Corrosion-fatigue had a significant impact on fatigue life as well as strength at lower
stress levels, but had no influence at higher stress levels. The endurance fatigue limit (EFL) reduced to 62.64 MPa and
raised to 64 MPa due to corrosion when using (SP) treatment.
Keywords
3.5%NaClcorrosion
AA6063-T6
constant fatigue loading
mechanical properties
shot peening (SP)
Keywords
3.5%NaClcorrosion
AA6063-T6
constant fatigue loading
mechanical properties
shot peening (SP)