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Micrestructure and property development in spray formed and extruded Al-Mg-Li-Zr alloys for aerospace and autosport applications

机译:用于航空航天和汽车运动的喷射成型和挤压成型的Al-Mg-Li-Zr合金的微结构和性能发展

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Low density Al-4Mg-1.3Li-0.4Zr and Al-6Mg-1.6Li-0.4Zr alloys were spray formed and the billets extruded under a range of conditions. The alloy compositions were selected to provide an attractive balance of tensile strength and elongation, without relying on complex post-processing and heat treatments - and are therefore suitable for complex cross section extrusions and free from quench distortion. The as-spray formed microstructures showed fine homogeneous, equiaxed grains with an average size of 10-15 urn. Firstly, a laboratory scale extrusion was carried out to extrude 30 mm diameter billets into 7.5 mm diameter cross-section and to investigate the effects of temperature and ram speeds on microstructural development. The micro-structure after extrusion at 400 ℃ was partially dynamically recrystallised with a -0.5 area fraction of ~1μm grains and the remainder were unrecrystallised elongated grains. Electron backscatter diffraction showed a mixed <111> + <100> double fibre texture. After peak age hardening at 150 ℃ for 96 h, the Al-6Mg-1.6Li-0.4Zr alloy showed a 0.2% proof strength of 495 MPa, a tensile strength of 553 MPa and elongation to failure of 8.5%; Al-4Mg-1.3Li-0.4Zr showed a 0.2% proof strength of 392 MPa, a tensile strength of 476 MPa and an elongation of 10%. Subsequently, large-scale complex cross-section were extruded at -400 ℃. Due to the complexity of the cross-sections and the non-axisymetric deformation, the fibre texture was distorted to FCC rolled Copper and Brass orientations. After a dual-step age hardening treatment of 130 ℃ for 8h followed by 160 ℃ for 8h, the proof strength, ultimate strength and elongations were 340 MPa, 470 MPa and 16% respectively. The combination of relatively simple process steps, high strength and ductility/formability, and low distortion in complex sections demonstrated the strong potential for these low density alloys in aerospace and autosport applications.
机译:将低密度的Al-4Mg-1.3Li-0.4Zr和Al-6Mg-1.6Li-0.4Zr合金喷涂成型,并在一定条件下挤压坯料。选择合金组合物以提供拉伸强度和伸长率的吸引人的平衡,而无需依赖复杂的后处理和热处理-因此适合于复杂的横截面挤压并且没有淬火变形。喷涂后形成的微观结构显示出细小的均匀等轴晶粒,平均尺寸为10-15微米。首先,进行了实验室规模的挤压,将直径为30毫米的坯料挤压成直径为7.5毫米的横截面,并研究了温度和冲压速度对微结构发展的影响。在400℃挤压后的显微组织局部动态地再结晶,晶粒的-0.5面积分数为〜1μm,其余为未结晶的长晶粒。电子反向散射衍射显示出混合的<111> + <100>双纤维织构。 Al-6Mg-1.6Li-0.4Zr合金在150℃时效时效硬化96 h后,其0.2%屈服强度为495 MPa,抗拉强度为553 MPa,断裂伸长率为8.5%。 Al-4Mg-1.3Li-0.4Zr的0.2%屈服强度为392 MPa,抗拉强度为476 MPa,伸长率为10%。随后,在-400℃下挤压出大型复杂截面。由于横截面的复杂性和非轴对称变形,纤维质地变形为FCC轧制的铜和黄铜取向。经过130℃8h,160℃8h的双步时效处理,屈服强度,极限强度和伸长率分别为340 MPa,470 MPa和16%。相对简单的工艺步骤,高强度和延展性/可成形性以及复杂截面中的低变形的结合证明了这些低密度合金在航空航天和自动运动应用中的强大潜力。

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