航空发动机钛合金材料的高周和超高周疲劳性能研究

李颖; 张成成; 高靖云; 任远; 李全通; 焦胜博

doi:10.6052/1000-0879-16-059

航空发动机钛合金材料的高周和超高周疲劳性能研究

1.
中航商用航空发动机有限责任公司, 上海商用飞机发动机工程技术研究中心, 上海 200241
2. 空军工程大学航空航天工程学院, 西安 710038

基金项目: 上海市科学技术委员会课题(13DJ1400200)和上海市“引进技术消化与吸收”专项资金(12XI-04)资助.

详细信息

通讯作者:
李颖,工程师,从事航空发动机先进材料及材料的动态力学性能研究.E-mail:liying@acae.com.cn

中图分类号: V412.4;V417
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出版历程
- 收稿日期: 2016-03-02
- 修回日期: 2016-03-29
- 发布日期: 2016-06-14

HIGH-CYCLE AND GIGA-CYCLE FATIGUE PROPERTIES OF TITANIUM ALLOY FOR AERO-ENGINE

1.
AVIC Commerical Aircraft Engine Co, Ltd, Shanghai Engineering Research Center of Commercial Aircraft Engine, Shanghai 200241, China
2. Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China

摘要

摘要: 通过对航空发动机空心风扇叶片用Ti-6Al-4V 随炉试样的高周和超高周疲劳试验研究,揭示了Ti-6Al-4V 材料在10⁷ 循环周次以上同样会发生疲劳破坏. 采用三参数幂函数寿命曲线拟合了高周和超高周的疲劳性能数据,发现可以较好地将两种试验下的数据衔接起来,结果显示在此试验条件下基于超声的超高周疲劳试验的频率效应可以忽略. 通过断口分析表明,超高周试样在试样表面没有缺陷的情况下,裂纹大多数是从材料内部或次表面萌生,而高周疲劳试样的裂纹是从材料表面开始萌生.
- 高周疲劳 /
- 超高周疲劳 /
- 疲劳性能 /
- 钛合金
Abstract: The high-cycle and giga-cycle fatigue properties of Ti-6Al-4V for hollow fan blade of aero-engine are investigated. The observations show that the Ti-6Al-4V may have fatigue failure above the 10⁷ cycles. The high-cycle and giga-cycle fatigue data are fitted by three parameter power function life curves. The data obtained by two test methods can be joined smoothly. It is concluded that the effect of frequency on giga-cycle fatigue properties under the test conditions is negligible. The fractograph of specimens is analyzed, which indicates that the giga-cycle specimens might generate internal fractures or surface fractures while there are not defects on the specimen surface, and the high-cycle specimens generate only surface fractures.
- high-cycle fatigue /
- giga-cycle fatigue /
- fatigue properties /
- titanium alloy

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参考文献(13)

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