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AI-Li合金的主要优点是比重小、弹性模量高、比刚度、比强度高。用于制造飞机结构件可以减轻飞机重量、节省燃料,提高飞行速度但是它的塑性和韧性较差。本文主要研究该合金在不同时效状态下裂纹萌生的机制、扩展途径和材料断裂行为。研究合金的成分(wt-%)为3.18Li,1.10Cu,0.84Mg,0.15Zr,0.31Fe,0.102Si,0.0041Mn,0.0061Ti,余量AI。合金在真空感应炉中熔炼,在氩气保护下浇铸。铸锭在500℃退火12h,车去外皮后在480℃用水压机压成20mm厚的板料,在500℃热轧成2mm厚的薄板。固熔处理用KNO_3作加热介质。520℃保温30分淬水,室温
AI-Li alloy’s main advantage is the proportion of small, high modulus of elasticity, stiffness, high strength. Used in the manufacture of aircraft structural components can reduce the weight of the aircraft, save fuel, improve flight speed but its poor ductility and toughness. In this paper, we mainly study the mechanism of crack initiation, propagation path and material fracture behavior of the alloy under different aging conditions. The composition (wt-%) of the investigated alloy was 3.18Li, 1.10Cu, 0.84Mg, 0.15Zr, 0.31Fe, 0.102Si, 0.0041Mn, 0.0061Ti, balance AI. The alloy is melted in a vacuum induction furnace and cast under argon protection. The ingot was annealed at 500 ℃ for 12h. After the car was removed from the sheath, the sheet was pressed into a 20mm thick sheet by a hydraulic press at 480 ℃. The sheet was hot rolled to a 2mm thick sheet at 500 ℃. Solid solution treatment with KNO_3 as a heating medium. 520 ℃ Insulation 30 minutes Quenching, room temperature