Light Alloys- Aluminium Heat Treatable Alloys Flashcards
Which Al alloys are heat treatable?
2xxx: Al-Cu(-Mg)
6xxx: Al-Mg-Si
7xxx: Al-Zn-Mg(-Cu)
8xxx: Al(-Li)
Trends for strength between different series
Strength increases 6xxx to 2xxx to 7xxx. Increased volume fraction of precipitates possible. Strength increases with increased alloying
What else does increased alloying do?
Decreases extrudability, weldability and corrosion resistance.
Trends for thermal stability between series
Thermal stability increases 7xxx to 6xxx to 2xxx. Reflects higher solubility and diffusivity of Zn then Si and Cu
What temperature are high temperature applications of Al at?
Around 200°C
2xxx series: applications, corrosion, additions, precipitation sequence
Aircraft structures and heavy engineering. First family of age hardenable alloys. Stress corrosion cracking and corrosion resistance poor so cladding sometimes used. Modern alloys have added Si to increase artificial ageing and added Mg to increase natural ageing. To get highest strengths cold work between quenching and artificial ageing. Precipitation sequence:
SSSS->lath GP zones->S’ laths->S laths
2xxx series ternary phase diagram
wt% Mg vs wt% Cu with dashed lines (like arcs) for different temperatures. High Cu:Mg ratio results in θ phase (Al2Cu) above certain temperature. Low Cu:Mg ratio results in S phase (Al2CuMg) above certain temperature. Very low Cu:Mg ratio give T phase but doesn’t tend to have commercial applications
Toughness vs yield strength for 2xxx and effect of tempers
Linear decrease in fracture toughness with increasing yield strength. T4 (natural ageing) given lower yield strength and higher fracture toughness than T6 (artificial ageing). However for T6 critical fracture stress is lower and so fast fracture will occur before yielding. T 4 has higher critical fracture stress than yield stress so the warning of plastic deformation occurs before fast fracture.
Formula for fracture toughness
Kc=Yσrt(πacrit)
Where Y is some constant
σ is yield stress?
a sub crit is critical crack length
Where is 2xxx series Al used on aircraft and why?
Airframe and skin structure. T4 is damage tolerant and used for lower wing skin. This is in tension so cracks tend to open and is prone to damage from material on runway
6xxx series: general uses and advantages over 2 and 7xxx
Accounts for 70% of extruded sections. Used in structural and architectural applications. General purpose medium strength heat treatable alloys. Advantages are: easily extruded at high speed, good anodisable surface finish, good corrosion resistance and weldability better than 2 or 7xxx, less dense than 2xxx
6xxx: disadvantages compared to 2 and 7xxx, other additions, precipitation sequence
Not as strong as 7xxx or as thermally stable as 2xxx. Add Cu to increase strength and Cr to restore corrosion resistance. T6 achieves 310MPa. Precipitation sequence:
SSSS->rod GP zones->β’ needles->equilibrium Mg2Si plates
What defines 6xxx as dilute or concentrate?
When Mg+Si < 1wt% is dilute
When Mg+Si > 1wt% is concentrate
Dilute 6xxx
Age well at room temperature (metastable GP zones). GP zones act as nucleation sites during artificial ageing (T6). Homogeneous distribution of Mg2Si precipitates.
Concentrate 6xxx
Initially higher strength were achieved by increasing Mg and Si content above 1wt%. Age well at room temperature (metastable GP zones). If carry out T6 artificial age strength is reduced. GP zones redissolve on heating so decrease in nucleation sites for Mg2Si precipitates. Need to age immediately after quenching (for artificial ageing) to get highest strength.