| DD6单晶合金的高温低周疲劳机制 |
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| 引用本文： | 李影,苏彬.DD6单晶合金的高温低周疲劳机制[J].航空动力学报,2003,18(6):732-736. |
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| 作者姓名： | 李影 苏彬 |
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| 作者单位： | 北京航空材料研究院25室,北京100095 |
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| 摘 要： | 本文研究了两种高温条件下三种多滑移取向的镍基单晶合金DD6的高温低周疲劳机制。结果表明,DD6合金低周疲劳裂纹以不同的机制在试样表面及亚表面上萌生,萌生位置与试验过程中的塑性应变幅及温度有关。对于001]取向,760℃和980℃温度条件的裂纹扩展面分别为沿{111}面的结晶学断裂面以及非结晶学断裂面。撕裂棱、裂纹前端微裂纹的桥接等因素是阻滞主裂纹扩展的主要机制。
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| 关 键 词： | 航空、航天推进系统 单晶高温合金 低周疲劳 裂纹萌生 裂纹扩展 |
| 文章编号： | 1000-8055(2003)06-0732-05 |
| 收稿时间： | 2003/1/24 0:00:00 |
| 修稿时间： | 2003年1月24日 |
Mechanisms of Low Cyclic Fatigue of DD6 Alloy at Elevated Temperature |
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| LI Ying and SU Bin.Mechanisms of Low Cyclic Fatigue of DD6 Alloy at Elevated Temperature[J].Journal of Aerospace Power,2003,18(6):732-736. |
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| Authors: | LI Ying and SU Bin |
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| Institution: | Beijing Institute of Aeronautical Materials,Beijing100095,China |
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| Abstract: | Low cycle fatigue mechanism of a single crystal nickel-base superalloy,DD6,has been investigated at 760℃ and 980℃.It was found that there were two kinds of sites where crack initiates,one being the surface of the specimens and the other being the sub-surface.Microcracks and oxide layer on the specimen surface are potential crack initiation sites in this superalloy.Secondary crack,reared ridge, and microcrack in the front of the main crack tip can all hinder crack propagation during low cycle fatigue. |
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| Keywords: | aerospace propulsion system single crystal superalloy low cycle fatigue crack initiation crack propagation |
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