摘要
简要介绍了某型直升机Ti1023钛合金中央件疲劳提前破坏的情况。本文从原始断口的电镜扫描、材料、加工工艺和熔滴的影响等方面分析,得出了"断口的高应力集中区附近存在熔滴是试验件提前破坏的主要原因,材料的疲劳极限值尚不满足要求也是试验件提前破坏的主要原因"的结论,并给出了改进建议。
Fatigue failure analysis of XX type helicopter main rotor Hub Ti1023 central components was introduced.We had analyzed the fracture section by scan electronic telescope and energy spectral analysis apparatus,measured the Ti1023 fatigue characteristic and the corrosion pits influence,analyzed the manufacture process of test parts,in this paper.In conclusion,the corrosion pits is a main reason and the Ti1023 fatigue characteristic is a key reason which leaded to failure of the test parts.Some improve advices was given in this paper,too.
出处
《直升机技术》
2008年第4期33-36,共4页
Helicopter Technique
关键词
钛合金材料
旋翼中央件
疲劳
titanium alloy
rotor hub central components
fatigue
