1. 中国航发北京航空材料研究院表面工程研究所,北京,100095
2. 中国航发北京航空材料研究院航空材料先进腐蚀与防护航空重点实验室,北京,100095
3. 中国航发北京航空材料研究院先进高温结构材料国防科技重点实验室,北京,100095
纸质出版:2020
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王欣, 许春玲,刘晨光,汤智慧,赵振业 . 喷丸对单晶合金中温疲劳性能的强化机制[J]. 航空制造技术, 2020, 63(12): 46-52.
WANG Xin, XU Chunling, LIU Chenguang,TANG Zhihui, ZHAO Zhenye. Strengthening Mechanism of Shot-Peening on Medium-Temperature Fatigue Property of Single-Crystal Superalloy. Aeronautical Manufacturing Technology, 2020, 63(12): 46-52.
王欣, 许春玲,刘晨光,汤智慧,赵振业 . 喷丸对单晶合金中温疲劳性能的强化机制[J]. 航空制造技术, 2020, 63(12): 46-52. DOI: 10.16080/j.issn1671-833x.2020.12.046.
WANG Xin, XU Chunling, LIU Chenguang,TANG Zhihui, ZHAO Zhenye. Strengthening Mechanism of Shot-Peening on Medium-Temperature Fatigue Property of Single-Crystal Superalloy. Aeronautical Manufacturing Technology, 2020, 63(12): 46-52. DOI: 10.16080/j.issn1671-833x.2020.12.046.
为研究喷丸对单晶合金中温疲劳性能的强化机制,采用陶瓷弹丸对单晶合金进行喷丸强化,研究了喷丸单晶合金表面形貌、截面微观组织、铸造微孔和 650℃ 旋转弯曲疲劳性能,并观察了疲劳断口。结果表明:喷丸强化后 650℃/Kt =1.7 和 650℃/Kt =3 旋转弯曲疲劳极限分别提高 21.3% 和 12.7%。首先,喷丸强化消除了表面尖锐的加工痕迹,形成了圆滑弹坑,将表面应力集中系数由 1.44 降低到 1.38,这是表面形貌优化机制。其次,喷丸单晶合金表面形成最表面的严重塑性形变层 – 次表面的线型形变层 – 里层的小塑性形变层 – 基体梯度塑性形变层。形变层最表面硬度较基体提高 42%,是形变强化机制。此外,在交变载荷下,2~10μm 的铸造微孔成为疲劳裂纹源;喷丸强化后铸造孔洞闭合或椭圆化,减小了孔洞位置的应力集中,喷丸对铸造孔洞的形变作用是第 3 个疲劳强化机制。
Ceramic shot were employed to shot-peen the single-crystal superalloy (SX) to analyze the strengthening mechanism of medium-temperature fatigue property. Surface morphology
cross-sectional micro-structure
casting porosities and 650℃ rotating-bending fatigue property were researched
and the fatigue fractures were observed. The results show the 650℃/Kt =1.7 and 650℃/Kt =3 rotating-bending fatigue limit increase by 21.3% and 12.7% after shot peening respectively. Firstly
shot peening eliminated sharp machining masks at the bottom and formed a smooth crater
which reduced the surface stress concentration factor from 1.44 to 1.38. This is the surface topography optimization mechanism. Secondly
a gradient plastic deformation layers were formed at the surface by shot peening
composed of the severe deformation layer at the outer-surface
the deformation layer with the “line structure” at the subsurface
the small deformation layer at the inferior surface and the matrix. The micro-hardness of the deformation layer was 42% higher than that of the matrix
which is the deformation strengthening mechanism. Furthermore
the as-received casting porosities with the diameter 2–10μm
could be the fatigue crack source during alternating stress. The micro-holes closed at the outer-surface and ovalized at the subsurface and inferior surface after at shot peening
which reduced the stress concentration at the casting porosities. The deformation effect on the casting micro-holes of shot peening is the third strengthening mechanism..
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