Modelling the Variability and the Anisotropic Behaviour of Crack Growth in SLM Ti-6Al-4V

The United States Air Force (USAF) Guidelines for the Durability and Damage Tolerance (DADT) certification of Additive Manufactured (AM) parts states that the most difficult challenge for the certification of an AM part is to establish an accurate prediction of its DADT. How to address this challenge is the focus of the present paper. To this end this paper examines the variability in crack growth in tests on additively manufactured (AM) Ti-6Al-4V specimens built using selective layer melting (SLM). One series of tests analysed involves thirty single edge notch tension specimens with five build orientations and two different post heat treatments. The other test program analysed involved ASTM standard single edge notch specimens with three different build directions. The results of this study highlight the ability of the Hartman-Schijve crack growth equation to capture the variability and the anisotropic behaviour of crack growth in SLM Ti-6Al-4V. It is thus shown that, despite the large variability in crack growth, the intrinsic crack growth equation remains unchanged and that the variability and the anisotropic nature of crack growth in this test program is captured by allowing for changes in both the fatigue threshold and the cyclic fracture toughness.

Automated summary

The study examines the variability in crack growth in AM Ti-6Al-4V specimens and highlights the ability of the Hartman-Schijve crack growth equation to capture this variability and anisotropic behavior. Despite the large variability in crack growth, the intrinsic crack growth equation remains unchanged, with changes in both the fatigue threshold and cyclic fracture toughness accounting for the variability and anisotropy observed in the test program.