| A357-T6铸造铝合金疲劳特性研究 |
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| 引用本文： | 朱成香,陈振中.A357-T6铸造铝合金疲劳特性研究[J].沈阳航空工业学院学报,2009,26(2). |
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| 作者姓名： | 朱成香 陈振中 |
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| 作者单位： | 沈阳航空工业学院航空宇航工程学院,辽宁,沈阳,110136 |
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| 摘 要： | 研究了A357-T6铸造铝合金在室温大气中正弦交变载荷下,应力比分别为r=-1,0.05和0.4时的疲劳特性.试验结果表明,A357-T6铸造铝合金的疲劳强度随应力比的增加而显著增加,疲劳极限分别是,应力比r=0.4时约为135MPa;应力比r=0.05时95MPa;而应力比为r=-1时70MPa.疲劳裂纹发生于试件表面或次表面铸造缺陷.裂纹沿着树状晶边界扩展.
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| 关 键 词： | A357-T6铸造铝合金 疲劳 断口 |
Fatigue properties study of A357-T6 casting aluminum alloy |
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| ZHU Cheng-xiang,CHEN Zhen-zhong.Fatigue properties study of A357-T6 casting aluminum alloy[J].Journal of Shenyang Institute of Aeronautical Engineering,2009,26(2). |
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| Authors: | ZHU Cheng-xiang CHEN Zhen-zhong |
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| Institution: | School of Aeronautical and Aerospace;Shenyang Institute of Aeronautical Engineering;Liaoning Shenyang 110136 |
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| Abstract: | The fatigue properties of A357-T6 casting aluminum alloy were studied at three stress ratios,r,of-1,0.05 and 0.4 in laboratory air at ambient temperature under load control with alternate sinusoidal wave form in this paper.The experimental results show that the fatigue strengths of A357-T6 casting aluminum alloy increase with increasing stress ratios,the fatigue limits are 135MPa for r=0.4,95MPa for r=0.05 and 70MPa for r=-1 respectively.Fatigue cracks initiated from defects at specimen surface or casting d... |
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| Keywords: | A357-T6 casting aluminum alloy fatigue fracture surface |
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