The effect of retrogression time during retrogression and re-aging (RRA) treatment of AA7010 is evaluated by performing tensile tests and characterizing the microchemistry of the grain boundary precipitates (GBPs) using transmission electron microscope coupled with the energy-dispersive spectroscopy. Retrogression time is evaluated so that the ultimate tensile strength of the RRA-treated sample is equal to that of the T6-treated sample and the grain boundary microstructure similar to that of the over-aged (T7451) condition. The investigation reveals that the sample retrogressed at 200 °C for 20 min has UTS of 586 MPa which is equivalent to that of the T6 sample and 11.5% higher than that of the T7451 condition. The fracture toughness of the...
The aging treatment effect on an AA6063 aluminum alloy was studied by characterizing the microstruct...
Heat treatable aluminum alloys such as 7075 and 7055, because of high strength and low density, are ...
We present the investigation of fatigue crack surface morphology and crystallographic grain orientat...
Aluminium alloy 7010 is subjected to retrogression and re-ageing (RRA) heat treatment to study the i...
Aluminium alloy 7010 is subjected to retrogression and re-ageing (RRA) heat treatment to study the i...
In this study, a retrogression process (R) has been applied to AA7075 at 180, 240, and 370°C for 15...
Aluminum alloys are widely used in aircraft structural components where light weight, high strength ...
Aircraft grade 7010 aluminum alloy was heat treated to two different conditions: (1) standard peak a...
In this study, aluminum alloy 7010 was subjected to three different ageing treatments i.e., peak age...
In this study, T651-applied AA7075 alloy was subjected to retrogression and reaging (RRA) process. V...
Industrial Summary: The 7075 aluminium alloy presents a low stress corrosion cracking strength when ...
Aluminum alloy 7075 is a very high strength material and have a wide range application throughout a...
Industrial Summary: The 7075 aluminium alloy presents a low stress corrosion cracking strength when ...
<p></p><p>ABSTRACT In this study, the effects of heat treatments in the peak aged (T6), overaged (T7...
The heat treatment of retrogression and re-ageing (RRA) has been applied to commercial alloy Al-7150...
The aging treatment effect on an AA6063 aluminum alloy was studied by characterizing the microstruct...
Heat treatable aluminum alloys such as 7075 and 7055, because of high strength and low density, are ...
We present the investigation of fatigue crack surface morphology and crystallographic grain orientat...
Aluminium alloy 7010 is subjected to retrogression and re-ageing (RRA) heat treatment to study the i...
Aluminium alloy 7010 is subjected to retrogression and re-ageing (RRA) heat treatment to study the i...
In this study, a retrogression process (R) has been applied to AA7075 at 180, 240, and 370°C for 15...
Aluminum alloys are widely used in aircraft structural components where light weight, high strength ...
Aircraft grade 7010 aluminum alloy was heat treated to two different conditions: (1) standard peak a...
In this study, aluminum alloy 7010 was subjected to three different ageing treatments i.e., peak age...
In this study, T651-applied AA7075 alloy was subjected to retrogression and reaging (RRA) process. V...
Industrial Summary: The 7075 aluminium alloy presents a low stress corrosion cracking strength when ...
Aluminum alloy 7075 is a very high strength material and have a wide range application throughout a...
Industrial Summary: The 7075 aluminium alloy presents a low stress corrosion cracking strength when ...
<p></p><p>ABSTRACT In this study, the effects of heat treatments in the peak aged (T6), overaged (T7...
The heat treatment of retrogression and re-ageing (RRA) has been applied to commercial alloy Al-7150...
The aging treatment effect on an AA6063 aluminum alloy was studied by characterizing the microstruct...
Heat treatable aluminum alloys such as 7075 and 7055, because of high strength and low density, are ...
We present the investigation of fatigue crack surface morphology and crystallographic grain orientat...