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| Residual Stresses of Al7050–T7451 Alloy Fastener Holes With Laser Shock Peening |
| SHUAI Shixiang 1 ，WU Junfeng 2 ，CHE Zhigang 2 ，CAO Ziwen 2 ，ZOU Shikun 2 ，SUN Rujian 2 |
1.AVIC Chengdu Aircraft Industrial (Group) Co., Ltd., Chengdu 610092, China;
2.AVIC Manufacturing Technology Institute，Beijing 100024，China |
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Abstract ABAQUS finite element model and life-death element technique were used to study the effects of different laser shock peening (LSP) paths on the residual stresses of Al7050–T7451 alloy fastener holes, which would improve their fatigue lives. Fastener holes were treated by LSP before and after opening holes by numerical simulation and test study. The results indicate that the simulation values of S11 surface compressive residual stresses of Al7050–T7451 fastener holes treated by LSP with four spots are close to the test values and the simulation values with hole after are close to the test values. It verifes the correctness of the model. Compared with hole before, the high S11 surface compressive residual stresses are generated at the edge of Al7050–T7451 alloy fastener holes with hole after. Compared with the two transverse spots, the high S11 surface compressive residual stresses are generated at the edge of Al7050–T7451 fastener holes treated by LSP with two longitudinal spots. Compared with two spots, the high S11 surface compressive residual stresses are generated at the edge of Al7050–T7451 fastener holes treated by LSP with four spots. The results could lay the foundation for the fatigue extension of fastener holes with LSP.
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2022, 
