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首页> 外文期刊>Fatigue & fracture of engineering materials and structures >Improved fatigue crack growth resistance by retrogression and re-aging heat treatment in 7010 aluminum alloy
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Improved fatigue crack growth resistance by retrogression and re-aging heat treatment in 7010 aluminum alloy

机译：通过回归和再时效热处理提高7010铝合金的抗疲劳裂纹扩展性

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摘要

Aircraft grade 7010 aluminum alloy was heat treated to two different conditions: (1) standard peak aging (T6) and (2) retrogression and re-aging (RRA). The microstructures of these alloys were characterized by using transmission electron microscope. Fatigue crack growth rate (FCGR) tests were conducted using standard compact tension specimens, following ASTM standards. Tests were conducted at various stress ratios, R ranging from 0.1 to 0.7. The RRA-treated alloy was observed to contain coarsened eta ' (MgZn2) precipitates with higher inter-particle spacing when compared with T6-treated alloy. The grain boundary precipitates (GBPs) were also coarsened and discontinuous in RRA-treated alloy as compared with continuous GBPs in T6 condition. The FCGR was lower and Delta K-th was higher in RRA-treated alloy compared with T6-treated alloy at all the stress ratios investigated. Improved fatigue crack growth resistance in RRA-treated alloy was correlated to the modified microstructure and enhanced crack closure levels.
机译：飞机级7010铝合金进行了两种不同的热处理：（​​1）标准峰值时效（T6）和（2）回归和时效（RRA）。利用透射电子显微镜对这些合金的显微组织进行了表征。疲劳裂纹扩展率（FCGR）测试是使用符合ASTM标准的标准紧凑型拉伸试样进行的。在各种应力​​比下进行测试，R的范围为0.1到0.7。与经T6处理的合金相比，经RRA处理的合金包含较粗的eta'（MgZn2）沉淀物，且颗粒间间距更高。与T6条件下连续的GBPs相比，在RRA处理的合金中，晶界沉淀物（GBPs）也被粗化和不连续。在所有研究的应力比下，与T6处理的合金相比，RRA处理的合金的FCGR较低，而Delta K-th较高。 RRA处理的合金改善的抗疲劳裂纹扩展性与改进的微观结构和增强的裂纹闭合水平相关。

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