Abstract
The traditional linear damage model cannot accurately describe the relationship between damage and load in the fatigue study of the aero-engine blade,thus causing unsatisfactory calculation result.The common non-linear damage model is easy to bring in error in the calculation due to neglecting the influence of torsional vibration.Therefore,based on the continuum damage theory,the non-linear damage model proposed by CHABOCHE is modified according to the blade material S-N curve obtained from the TC4(Ti-6Al-4V)fatigue testing,and the non-linear continuum damage model is proposed and its correctness is verified.In comparison with the experimental data and the linear damage model results,the non-linear continuum damage model shows better accuracy in reflecting the damage accumulation process.Finally,the non-linear continuum damage model is used to predict the fatigue life of a certain aero engine blade.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
