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Fatigue lifetime assessment and crack propagation of Ni-based VDM Alloy 699 XA produced by additive manufacturing
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SYSNO ASEP 0582279 Document Type C - Proceedings Paper (int. conf.) R&D Document Type Conference Paper Title Fatigue lifetime assessment and crack propagation of Ni-based VDM Alloy 699 XA produced by additive manufacturing Author(s) Vražina, Tomáš (UFM-A)
Šulák, Ivo (UFM-A) ORCID
Nowak, B. (DE)
Verma, B. (DE)
Krupp, U. (DE)
Kruml, Tomáš (UFM-A) RID, ORCIDNumber of authors 6 Source Title Procedia Structural Intergrity, 52. - Amsterdam : Elsevier, 2024 / Aliabadi M. ; Khodaei Z. S. - ISSN 2452-3216 Pages s. 43-51 Number of pages 9 s. Publication form Online - E Action FDM 2023 - International Conference on Fracture, Damage and Structural Health Monitoring /21./ Event date 12.09.2023 - 14.09.2023 VEvent location London Country GB - United Kingdom Event type WRD Language eng - English Country NL - Netherlands Keywords Additive manufacturing ; VDM 699 XA ; Paris law ; fatigue life performance ; fatigue crack propagation Subject RIV JG - Metallurgy OECD category Materials engineering Institutional support UFM-A - RVO:68081723 EID SCOPUS 85186675232 DOI 10.1016/j.prostr.2023.12.005 Annotation The present work focuses on the low-cycle fatigue (LCF) behavior of conventionally and additively manufactured (laser powder
bed fusion (LPBF) technique, Ni-based VDM Alloy 699 XA. LCF tests were performed on miniature cylindrical specimens in a
symmetrical push-pull cycle under strain control with a constant total strain amplitude at 23°C. Cyclic hardening/softening curves,
cyclic stress-strain curves, and fatigue life curves were obtained. Despite the present manufacturing defects associated with the
LPBF technology, the fatigue lifetime of the LPBF manufactured material is higher than that of conventionally prepared material.
Fatigue crack initiation sites and fatigue crack propagation areas were investigated by means of scanning electron microscopy
(SEM). A quantitative fractography of fracture surfaces was introduced to provide a detailed description of fatigue crack growth
from the evaluation of striation spacing. The dependency of the stress intensity factor range on macroscopic crack growth rates was
displayed in the form of the Paris Law. The differences in fatigue lifetimes and fatigue crack growth rates of additively
manufactured and hot rolled solution annealed alloy 699 XA plate material were discussed and correlated with respect to the
microstructural specifics of both material batches.Workplace Institute of Physics of Materials Contact Yvonna Šrámková, sramkova@ipm.cz, Tel.: 532 290 485 Year of Publishing 2025
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