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Most stress corrosion cracking (SCC) mechanisms initiate from localised corrosion (pitting, intergranular attack, de-alloying), which provides local stress concentration. Alloys are generally more susceptible to SCC than pure metals because selective dissolution or oxidation is possible. De-alloying involves the selective dissolution of the less noble (LN) component from an alloy. The more noble (MN) component enriches on the surface forming a brittle, metallic, nanoporous layer. In noble metal alloys and brass, SCC shows correlation with the threshold LN content below which de-alloying stops (the parting limit). In Fe-Ni-Cr engineering alloys de-alloying may be responsible for Cl-SCC, although this has not been proven explicitly. Initial indications show that de-alloying causes SCC in hot, caustic environments. In some cases, Ni enrichment and porosity are associated with cracks in stainless steel after long-term service in nuclear high temperature water environments, but it is unclear if this plays a causal role in cracking. Here the de-alloying mechanism (primarily the effect of Ni (MN) content) and its relationship to SCC in Fe-Ni-Cr materials (Fe10Ni, 310SS and Alloy 800) is examined using a hot caustic environment, and compared to classical de-alloying systems. De-alloyed layers formed on all materials, although Alloy 800 required a higher temperature. Increasing Ni content improved de-alloying resistance according to classical theory. Unlike classical systems, de-alloying occurred with concurrent MN dissolution and, at open circuit potential (OCP), the layers retained significant Fe and Cr (LN) instead of being ‘almost pure’ MN. Layers formed with applied anodic potential were friable and highly LN depleted. This behaviour was successfully modelled in Kinetic Monte Carlo simulations. Recently, it has been shown that SCC in noble element alloys depends on the mechanical integrity (quality) of the de-alloyed layer; a finding that was reflected here. At 140 °C at OCP the layer on 310SS was too thin to promote SCC and Alloy 800 did not de-alloy significantly. Layers formed with anodic potential did not result in SCC. In 50% NaOH at 280 °C, severely stressed 310SS cracked where thick de-alloyed layers formed. However, the thin layer formed on Alloy 800 was associated with SCC, even with low residual stress.

Most stress corrosion cracking (SCC) mechanisms initiate from localised corrosion (pitting, intergranular attack, de-alloying), which provides local stress concentration. Alloys are generally more susceptible to SCC than pure metals because selective dissolution or oxidation is possible. De-alloying involves the selective dissolution of the less noble (LN) component from an alloy. The more noble (MN) component enriches on the surface forming a brittle, metallic, nanoporous layer. In noble metal alloys and brass, SCC shows correlation with the threshold LN content below which de-alloying stops (the parting limit). In Fe-Ni-Cr engineering alloys de-alloying may be responsible for Cl-SCC, although this has not been proven explicitly. Initial indications show that de-alloying causes SCC in hot, caustic environments. In some cases, Ni enrichment and porosity are associated with cracks in stainless steel after long-term service in nuclear high temperature water environments, but it is unclear if this plays a causal role in cracking. Here the de-alloying mechanism (primarily the effect of Ni (MN) content) and its relationship to SCC in Fe-Ni-Cr materials (Fe10Ni, 310SS and Alloy 800) is examined using a hot caustic environment, and compared to classical de-alloying systems. De-alloyed layers formed on all materials, although Alloy 800 required a higher temperature. Increasing Ni content improved de-alloying resistance according to classical theory. Unlike classical systems, de-alloying occurred with concurrent MN dissolution and, at open circuit potential (OCP), the layers retained significant Fe and Cr (LN) instead of being ‘almost pure’ MN. Layers formed with applied anodic potential were friable and highly LN depleted. This behaviour was successfully modelled in Kinetic Monte Carlo simulations. Recently, it has been shown that SCC in noble element alloys depends on the mechanical integrity (quality) of the de-alloyed layer; a finding that was reflected here. At 140 °C at OCP the layer on 310SS was too thin to promote SCC and Alloy 800 did not de-alloy significantly. Layers formed with anodic potential did not result in SCC. In 50% NaOH at 280 °C, severely stressed 310SS cracked where thick de-alloyed layers formed. However, the thin layer formed on Alloy 800 was associated with SCC, even with low residual stress.

The stress corrosion cracking (SCC) behaviour of Mg alloy AZ31B was investigated with respect to surface condition. Salt fog U-bend testing was used to identify changes in SCC as a result of surface conditioning pre-treatments. Six surface conditions were investigated: as-received, mechanically-polished, sulphuric acid (H2SO4)-cleaned, mechanically-polished then H2SO4-cleaned, aged H2SO4-cleaned, and acetic acid (C2H4O2)-cleaned. Results showed that the rate of SCC was accelerated and the SCC mode was intergranular for all surface conditioning treatments involving H2SO4-cleaning. It was found that the accelerated intergranular SCC was a result of three contributing factors: a low pH, the presence of aggressive ions, and a porous film which allowed direct contact between the metal surface and the electrolyte. Characterization of the surfaces using potentiodynamic polarization and cross-sectional images of sample surfaces showed that in the absence of one of these three contributing factors intergranular SCC would not occur. / Thesis / Master of Applied Science (MASc)

Aluminum-magnesium alloy (AA5083-H116) is primarily designed for marine applications such as in ship hulls and deckhouses. Its excellent combination of physical and mechanical properties makes it useful for other applications such as aircraft construction, military equipment and vehicles and automobiles.<p>This study investigated the effect of time and temperature of sensitization on the mechanical and chemical properties of AA5083-H116 such as tensile strength, yield strength and susceptibility to intergranular corrosion (IGC). Test specimens were sensitized at various temperatures (80oC, 100oC, 175oC and 200oC) for up to 672 h (4 weeks). Microhardness measurements, tensile testing, scanning electron microscopy (SEM), energy dispersive X-ray spectrometry (EDS), inductively coupled plasma/mass spectrometry (ICP/MS) and nitric acid mass loss tests (NAMLT) were used to evaluate these effects. <p>The results obtained show that the mechanical properties of AA5083-H116 deteriorated with increasing sensitization temperature and time. The adverse effect on these properties was attributed to reduction in dislocation density and recrystallization at higher temperatures. The as-received specimens and those sensitized at 80oC showed no susceptibility to IGC. However, at higher sensitization temperatures and longer resident times, resistance to IGC decreased dramatically. The reduction in IGC resistance was attributed to precipitation of secondary phases along the grain boundaries.

Aluminum-magnesium alloy (AA5083-H116) is primarily designed for marine applications such as in ship hulls and deckhouses. Its excellent combination of physical and mechanical properties makes it useful for other applications such as aircraft construction, military equipment and vehicles and automobiles.<p>This study investigated the effect of time and temperature of sensitization on the mechanical and chemical properties of AA5083-H116 such as tensile strength, yield strength and susceptibility to intergranular corrosion (IGC). Test specimens were sensitized at various temperatures (80oC, 100oC, 175oC and 200oC) for up to 672 h (4 weeks). Microhardness measurements, tensile testing, scanning electron microscopy (SEM), energy dispersive X-ray spectrometry (EDS), inductively coupled plasma/mass spectrometry (ICP/MS) and nitric acid mass loss tests (NAMLT) were used to evaluate these effects. <p>The results obtained show that the mechanical properties of AA5083-H116 deteriorated with increasing sensitization temperature and time. The adverse effect on these properties was attributed to reduction in dislocation density and recrystallization at higher temperatures. The as-received specimens and those sensitized at 80oC showed no susceptibility to IGC. However, at higher sensitization temperatures and longer resident times, resistance to IGC decreased dramatically. The reduction in IGC resistance was attributed to precipitation of secondary phases along the grain boundaries.

No description available.

No description available.

No description available.