| A357-T6铸造铝合金疲劳裂纹扩展特性研究 |
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| 引用本文： | 徐芳,陈振中.A357-T6铸造铝合金疲劳裂纹扩展特性研究[J].飞机设计,2009,29(2). |
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| 作者姓名： | 徐芳 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铸造铝合金在应力比R=0.05及应力比R=0.7时的疲劳裂纹扩展行为.应力比R=0.7的裂纹扩展速率比应力比R=0.05的裂纹扩展速率快,这是由于应力比R=0.05时断口表面粗糙引起的裂纹闭合效应,降低了裂纹尖端的有效驱动力.断口表面的脱粘共晶Si颗粒和Si颗粒脱落后形成的凹坑表明裂纹沿着树状晶边界扩展.
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| 关 键 词： | A357铸造铝合金 裂纹扩展 断口形貌 |
The Study on Fatigue Crack Propagation Behavior of A357-T6 Casting Aluminum Alloys |
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| XU Fang,CHEN Zhen-zhong.The Study on Fatigue Crack Propagation Behavior of A357-T6 Casting Aluminum Alloys[J].Aircraft Design,2009,29(2). |
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| Authors: | XU Fang CHEN Zhen-zhong |
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| Institution: | School of Aeronautical & Aerospace;Shenyang Institute of Aeronautical Engineering;Shenyang 110136;China |
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| Abstract: | Fatigue crack propagation behaviors under stress radio R=0.05 and R=0.7 in A357-T6 casting Aluminum Alloys were studied.The fatigue crack propagation rate da/dN is faster at R=0.7 than that of R=0.05 because of crack closure due to crack surface roughness at R=0.05,which reduced the driving force of crack tip.The decohesion of eutectic Si particles and the holes appeared on the crack surface show that fatigue crack grows along dendrite boundary. |
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| Keywords: | A357 casting aluminum alloy crack propagation fracture surface |
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