利用维氏硬度检测、疲劳性能测试、视差量热法(DSC)、透射电子显微分析(TEM)等手段,研究了航空用T3态2E12铝合金在150℃下分别暴露10 h,100 h,1000 h组织演变及疲劳寿命变化规律.结果表明:随热暴露时间的增加,合金硬度不断增大,疲劳寿命呈先增后降趋势;T3态及热暴露10 h合金中析出相由GPB区结构组成,热暴露10 h合金中GPB区发生长大,因而具有最长疲劳寿命;热暴露100 h至1000 h后,合金中析出相为S"相及S'相,析出相在晶界处析出,晶界附近形成无沉淀析出带(PFZ);由于S"相及S'相共格性较GPB区低,加之晶界处析出相易形成裂纹源,PFZ与基体协调性差等因素,热暴露100 h和1000 h后,合金疲劳寿命急剧下降.
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