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Evaluation of Residual Stress Distribution and Relaxation on In Situ TiB2/7050 Al Composites

The Key Laboratory of Contemporary Design and Integrated Manufacturing Technology, Ministry of Education, Northwestern Polytechnical University, Xi’an 710072, China
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Materials 2018, 11(5), 706; https://doi.org/10.3390/ma11050706
Received: 2 February 2018 / Revised: 15 March 2018 / Accepted: 24 April 2018 / Published: 30 April 2018
(This article belongs to the Section Advanced Composites)
Interior residual stresses induced by quenching may cause distortion during subsequent machining processes. Hence, various strategies have been employed to relieve the interior residual stress, such as stretching, post treatment, and other techniques. In this study, the stress distribution inside TiB2/7050 Al composite extrusions was investigated and the effects of different methods on relieving the quenching-induced stress were compared. Firstly, three TiB2/7050 Al composite extrusions were treated by stretching, stretching and heat treatment, and stretching and cold treatment processes, respectively. Then, the multiple-cut contour method was employed to assess the residual stresses in the three workpieces. Experimental results indicate that the interior stress of TiB2/7050 Al composite extrusions after stretching ranges from −89 MPa to +55 MPa, which is larger than that in 7050 aluminum alloy, which ranges from −25 Pa to +25 MPa. The heat treatment performs better than the cold treatment to reduce the post-stretching residual stress, with a reduction of 23.2–46.4% compared to 11.3–40.8%, respectively. From the stress map, it is found that the stress distribution after the heat treatment is more uniform compared with that after the cold treatment. View Full-Text
Keywords: residual stress; metal matrix composites; contour method residual stress; metal matrix composites; contour method
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Lin, K.; Wang, W.; Jiang, R.; Xiong, Y.; Zhao, D. Evaluation of Residual Stress Distribution and Relaxation on In Situ TiB2/7050 Al Composites. Materials 2018, 11, 706.

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