Volume 29 Issue 7
Jul.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  (7): 1567-1573
LI Jiu-kai, LIU Yong-jie, WANG Qing-yuan, HOU Fang. High-temperature ultra-high cycle fatigue test of TC17 titanium alloy[J]. Journal of Aerospace Power, 2014, (7): 1567-1573. doi: 10.13224/j.cnki.jasp.2014.07.008
Citation: LI Jiu-kai, LIU Yong-jie, WANG Qing-yuan, HOU Fang. High-temperature ultra-high cycle fatigue test of TC17 titanium alloy[J]. Journal of Aerospace Power, 2014, (7): 1567-1573. doi: 10.13224/j.cnki.jasp.2014.07.008
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High-temperature ultra-high cycle fatigue test of TC17 titanium alloy

doi: 10.13224/j.cnki.jasp.2014.07.008

  • 1. Key Laboratory of Ministry of Education for Energy Engineering Safety and Disaster Mechanics, College of Architecture and Environment, Sichuan University, Chengdu 610065, China;

  • 2. School of Aeronautics and Astronautics, Sichuan University, Chengdu 610065, China

  • Received Date: 2013-10-27
  • Publish Date: 2014-07-28
    Abstract
  • A high-temperature ultrasonic fatigue testing system was self-developed to evaluate the ultra-high cycle fatigue properties of TC17 titanium alloy. Ultrasonic (20 kHz) fatigue tests were performed at room temperature, 200℃ and 350℃, respectively. The result shows that dynamic modulus of elasticity of TC17 titanium alloy decreases linearly with increasing temperature. The S-N curve presents a continuously descending shape at room temperature. While at 200℃ and 350℃, inflexion points of S-N curves can be observed clearly at fatigue life of 107 cycles. In addition, the results show that the fatigue cracks initiate from the surface or sub-surface of specimen and the interior crack initiation is not found. It indicates that the crack initiation of TC17 titanium alloy can be independent of interior inclusion or defect. Both the crack initiation and the crack propagation are promoted at high-temperature.

     

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