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Observation of fatigue damage process in SiC fiber-reinforced Ti-15-3 composite at high temperature

机译:SiC纤维增强Ti-15-3复合材料高温疲劳损伤过程的观察

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摘要

Unnotched SiC (SCS-6) fiber-reinforced Ti-15-3 alloy compositeis subjected to a tension-tension fatigue test in a vacuum of2×10 –3 Pa at 293 and 823 K with a frequency of 2 Hz and R=0.1.Direct observation of the damage evolution process during thetest is carried out by scanning electron microscopy (SEM). Testtemperature dependent and independent fatigue damage behaviorsare observed. The early stage fiber fractures observed at thepolished surface are not influenced by the testtemperature;however, matrix crack initiation and propagationbehaviors differ greatly with temperature. The evolution ofinterface wear damage also differs with temperature, becomingmore severe at 823 K, and the interface wear damage zoneincreases with the increase of the number of fatigue cycles. Themacroscopic fatigue damage appears as a modulus reductionassociated with interface sliding, matrix crack propagation,and plastic deformation of the matrix. The deformation zone ofthe composite tested at 823 K spreads more than that at 293 K.The fatigue life of the composite tested at 823K is longer thanthat at 293K. This behavior is related to the difference inspread of the damage zone in the matrix.
机译:无缺口SiC(SCS-6)纤维增强Ti-15-3合金复合材料在2×10 –3 Pa的真空中于293和823 K于2 Hz的频率和R = 0.1的条件下进行拉伸疲劳试验。通过扫描电子显微镜(SEM)可以直接观察测试过程中的损伤演变过程。观察到依赖于测试温度和独立于疲劳的行为。在抛光表面观察到的早期纤维断裂不受测试温度的影响;但是,基体裂纹的萌生和扩展行为随温度的不同而有很大差异。界面磨损损伤的发展也随温度而变化,在823 K时变得更严重,并且随着疲劳循环次数的增加,界面磨损损伤区域也增加。宏观疲劳损伤表现为与界面滑动,基体裂纹扩展和基体塑性变形相关的模量降低。在823 K下测试的复合材料的变形区比在293 K下扩展的更大。在823K测试的复合材料的疲劳寿命比在293K下的疲劳寿命更长。此行为与矩阵中损坏区域的差异扩展有关。

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