Evolution of Oxygen-Rich Layer and Its Effect on Fatigue Property of Ti-6Al-4V

LIU Yunxi; CHEN Wei; LIU Jie; LI Zhiqiang

doi:10.16080/j.issn1671-833x.2018.11.074

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Evolution of Oxygen-Rich Layer and Its Effect on Fatigue Property of Ti-6Al-4V

更新时间：2025-10-30

- Evolution of Oxygen-Rich Layer and Its Effect on Fatigue Property of Ti-6Al-4V
- Aeronautical Manufacturing Technology Vol. 61, Issue 11, Pages: 74-78(2018)
- 作者机构：
  
  1. 中国航空制造技术研究院,北京,100024
  2. 塑性成形技术航空科技重点实验室,北京,100024
  3. 数字化塑性成形技术及装备北京市重点实验室,北京,100024
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2018.11.074
  CLC：
- Published：2018
- 稿件说明：
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刘运玺1,2,3，陈玮1，刘杰4，李志强1,2,3，姚罡1，韩秀全1,2,3. Ti-6Al-4V 富氧层生长规律及对疲劳性能的影响[J]. 航空制造技术, 2018, 61(11): 74-78.

LIU Yunxi1,2,3, CHEN Wei1, LIU Jie4, LI Zhiqiang1,2,3, YAO Gang1, HAN Xiuquan1,2,3. Evolution of Oxygen-Rich Layer and Its Effect on Fatigue Property of Ti-6Al-4V. Aeronautical Manufacturing Technology, 2018, 61(11): 74-78.
刘运玺1,2,3，陈玮1，刘杰4，李志强1,2,3，姚罡1，韩秀全1,2,3. Ti-6Al-4V 富氧层生长规律及对疲劳性能的影响[J]. 航空制造技术, 2018, 61(11): 74-78. DOI： 10.16080/j.issn1671-833x.2018.11.074.

LIU Yunxi1,2,3, CHEN Wei1, LIU Jie4, LI Zhiqiang1,2,3, YAO Gang1, HAN Xiuquan1,2,3. Evolution of Oxygen-Rich Layer and Its Effect on Fatigue Property of Ti-6Al-4V. Aeronautical Manufacturing Technology, 2018, 61(11): 74-78. DOI： 10.16080/j.issn1671-833x.2018.11.074.

摘要

研究了Ti-6Al-4V 合金在900℃、930℃ 和960℃下富氧α 层显微组织和显微硬度的变化及对疲劳行为的影响。在热暴露0.5~24h 时间内，富氧层中的α 相含量远高于基体内部，其晶粒尺寸也发生长大现象。随着热暴露温度的升高和时间的延长，富氧α 层的厚度增大，氧的固溶强化作用使其显微硬度明显升高。显微硬度随着深度的增加逐渐下降，在表面200μm以下趋于稳定。热暴露后疲劳试样表面的富氧层造成疲劳裂纹萌生模式发生改变，由单裂纹源刻面萌生模式变为多裂纹源表面萌生，裂纹萌生阶段寿命与总寿命均大幅降低。

Abstract

The microstructure and microhardness of Ti-6Al-4V α-case which experiences thermal exposure at 900℃

930℃ and 960℃ are investigated. After thermal exposure of 0.5-24h

the volume fraction of α is much higher in α-case than in sample interior

and the grains grow larger comparing with the original material. The α-case thickness increases with time and temperature increasing. Due to the strengthening effect of oxygen

the microhardness of α-case thickness also increases. The microhardness value decreases from the surface to the interior of the sample

and it becomes stable below 200μm. The α-case on the fatigue sample induces a multi-site fatigue crack initiation mode

which leads to a significant deterioration of fatigue life.

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