期刊文献+

Stress-controlled LCF experiments and ratcheting behaviour simulation of a nickel-based single crystal superalloy with [001] orientation 被引量:3

原文传递
导出
摘要 Uniaxial ratcheting behaviour and low cycle fatigue(LCF)failure mechanism of nickel-based single crystal superalloy DD6 with[001]orientation are investigated through the stresscontrolled LCF tests with stress ratio of-1.Then the deformation behaviour during the wholelifetime from the beginning of the experiment to the fracture of the specimen,as well as the fractographic/metallographic morphology,are compared with the strain-controlled LCF experimental results.Through the scanning electron microscope(SEM)observations,it is shown that the failure characteristics under stress-controlled LCF loading are similar with those under strain-controlled loading.Nevertheless,unlike strain-controlled LCF loading,even under fully reversed cycle loading for stress-controlled LCF,DD6 shows significant ratcheting behaviour due to the tensioncompression asymmetry.In addition,the LCF lifetimes under stress control are significantly shorter than the LCF lifetimes under strain control,and the culprit might be the detrimental effect of ratcheting strain on LCF lifetime.Based on these phenomena,an improved crystal plasticity constitutive model on the basis of slip-based Walker constitutive model is developed through modifying the kinematic hardening rule in order to overcome the inaccurate prediction of decelerating stageand stable stage of ratcheting behaviour.Furthermore,combining the continuum damage mechanics,a damage-coupled crystal plasticity constitutive model is proposed to reflect the damage behaviour of DD6 and the accelerating stage of ratcheting behaviour.The simulation results for the stress-controlled LCF deformation behaviour including the whole-lifetime ratcheting behaviour show good agreement with the experimental data.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第8期112-121,共10页 中国航空学报(英文版)
基金 financial support from National Natural Science Foundation of China(Nos.51875020,51675024 and 51811540406) National Science and Technology Major Project(No.2017-IV-0004-0041) Aviation Science Foundation of China(No.6141B090314) Academic Excellence Foundation of BUAA。
  • 相关文献

参考文献5

二级参考文献50

  • 1王洪斌.涡轮叶片热/机械复合疲劳试验方法研究[J].航空发动机,2007,33(2):7-11. 被引量:13
  • 2Morrison J L M, Shepherd W. Proc Inst Mech Eng, 1950; 163:1.
  • 3Marin J, Hu L W. ASME Trans, 1956; 78:499.
  • 4Marin J, Sauer J A. J Franklin I, 1953; 256:119.
  • 5Yang N S. Acta Mech Sin, 1958; 2:43.
  • 6Frederick C O, Armstrong P J. Mater High Temp, 2007; 24:1.
  • 7Jiang Y, Kurath P. Int J Plast, 1996; 12:387.
  • 8Chaboche J L. Int J Plast, 1986; 2:149.
  • 9Chaboche J L. Int J Plast, 2008; 24:1642.
  • 10Ohno N, Wang J D. Int J Plast, 1993; 9:375.

共引文献22

同被引文献18

引证文献3

二级引证文献1

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部