Abstract
In industry, post-process heat treatments of Ti-6Al-4V are performed with the aim of improving its tensile behaviour. While heat treatments of wrought Ti6Al4V have been standardised (e.g., Aerospace Material Specification H-81200), heat treatments of selective laser melting (SLM)-produced Ti-6Al-4V lacks research and understanding. Significant concern exists about SLM Ti6-Al-4V’s achievable ductility attributed to its martensitic (α’) phase. In this research, heat treatments at a range of temperatures are applied to SLM-produced Ti-6Al-4V tensile samples. Microstructural analysis (both optically and through electron backscatter diffraction) was used to identify links between heat treatments and microstructure. Subsequently, uniaxial tensile tests were performed to determine the respective tensile properties of all samples. Correlations in the data show a significant loss in strength with respect to an increase in annealing temperature due to grain growth, while no noticeable trend was observed for fracture strain with regard to annealing temperatures.Â
Highlights
The industry of additive manufacturing (AM) has grown exponentially since 2006
A popular AM technique used for the manufacturing of metallic parts for application in the biomedical and aerospace industries is selective laser melting (SLM) — a metal additive manufacturing (MAM) technique that has advantages in a wide range of applicable areas
The aim of this research is to contribute to the limited understanding of the link between SLM Ti6Al-4V microstructure and heat treatments at various temperatures, as well as the achievable tensile properties of these ‘typical’ SLM Ti-6Al-4V heat treatments
Summary
The industry of additive manufacturing (AM) has grown exponentially since 2006. This growth can be attributed, among others factors, to the development and improvement of the technology and thereby the improvement of the achievable quality of manufactured parts. Part ductility (percentage elongation-to-break) is of particular concern, since research has found the elongation-to-break (fracture strain) to be below the 10 per cent American Standard Test Method (ASTM) limit [3] (ASTM F2924–14) to qualify for use in biomedical [4] and aerospace industries (Aerospace Material Standard (AMS) 4911). It is well-established that mechanical properties depend on microstructure [5]. Controlling the mechanical and material properties of SLMproduced Ti-6Al-4V is not as well-established as standard methods such as wrought and cast parts, and it requires research and development
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