航空结构件铝合金固溶时效性能研究

Study on Solution and Aging Properties of Aluminum Alloy for Aeronautical Structural Parts

研究了航空结构件常用铝合金的热处理性能,确定合适的热处理工艺、零件最佳装料方式和淬火冷却介质。对2024铝合金进行热处理至T6态和T8态,分析比较了加热区域内不同位置和不同状态材料的力学性能和耐腐蚀性能。结果表明:力学性能最低点出现在加热区域中心位置,T6态材料在中心位置的抗拉强度69.5 Ksi,屈服强度56 Ksi,延伸率10%;T8态材料在中心位置的抗拉强度68.5 Ksi,屈服强度62 Ksi,延伸率8%。中心位置不同状态材料的腐蚀性能有所差异,中心位置材料最大晶间腐蚀深度分别为119μm(T6水冷却)、77μm(T6聚合物冷却)和96μm(T8),晶间腐蚀区域面积比例分别为36.9%(T6水冷却)、19.6%(T6聚合物冷却)和47.9%(T8),水淬比聚合物淬火引起的材料腐蚀现象要明显,聚合物冷却特性比水冷却特性要好。

The heat treatment properties of aluminum alloys commonly used as aeronautical structural parts are studied,the appropriate heat treatment process,the best loading method and quenching medium are determined.The 2024 aluminum alloy is heat treated to T6 and T8 state.The mechanical properties and corrosion properties of materials in different position and states in the heating area are analyzed and compared.The results show that the lowest point of mechanical properties is the center of the heating area,the tensile strength,yield strength and elongation of T6 state material in the center are 69.5 Ksi,56 Ksi and 10%.The tensile strength,yield strength and elongation of T8 state material in the center are 68.5 Ksi,62 Ksi and 8%.The corrosion properties of materials with different states in the centra are different.The maximum intergranular corrosion depth is 119μm(T6 water quenching),77μm(T6 polymer quenching)and 96μm(T8)respectively.The area proportion of intergranular corrosion is 36.9%(T6 water quenching),19.6%(T6 polymer quenching)and 47.9%(T8)respectively.The corrosion phenomenon caused by water quenching is more obvious than that caused by polymer quenching,and the polymer cooling characteristic is better than water cooling.