Additive manufacturing (AM) is “a process of joining materials to obtain components from 3D model data using a layer upon layer approach” [
1‐
5]. This approach enables the successful production of parts without design constraints, allowing the integration of components and the use of topologically optimized and lightweight structures [
6‐
8]. Therefore, over the past years, various companies and industrial sectors have applied this technology to benefit from its advantages [
9,
10]. In general, metal AM processes can be divided into directed energy deposition (DED) and powder bed fusion (PBF) processes [
11]. Among the latter, the electron beam melting (EBM) process, as a PBF method, has received considerable interest in the aerospace and medical sectors [
10,
12]. The main driver for aerospace applications is represented by the possibility to process the materials that their processability with the other technologies faced with several challenges [
13]. Regarding the medical sector, the EBM process is able to produce tailored implants, ensuring better bio-compatibility and improving the interaction between the prosthesis and prior tissues [
14,
15].
Ti-6Al-4V is one of the most processed materials by EBM technology, which can open new doors in the manufacturing of this particular alloy [
16]. Traditionally, Ti-6Al-4V parts suffer from high-density inclusions (HDI), low-density inclusions (LDI) and surface oxidation [
17]. The EBM process can avoid the first two defects mentioned above and limit the latter due to its vacuum working conditions [
16]. On the other hand, during the production of Ti-6Al-4V alloy via the EBM process due to the presence of a preheating phase before the melting, the temperature inside the building chamber reaches values of 650–750 °C for this specific alloy [
16,
18,
19]. These working conditions ensure small thermal shrinkages, and the powder bed results in enough strength to support the construction of the overhang part and limiting the use of supports [
20,
21]. Therefore, EBM makes possible the production of so-called micro-architectured components. These parts, also known as cellular structures, are of considerable interest because of the opportunity to achieve a singular combination of lightness and high mechanical properties compared to their corresponding bulk ones [
22,
23]. In general, this class of materials includes foams and lattice structures [
24]. Lattice structures are widely produced by EBM thanks to the possibility to achieve high specific strength [
25], oxidation resistance [
25,
26] and biocompatibility with the human tissues [
14,
26,
27]. These structures, also known as cellular, reticulated or truss, have been defined as repetitions in a unit elementary cell [
22]. The three main factors affecting the properties of cellular solids that have been identified by Ashby [
28] are: (1) the material of which is made, (2) the cell topology and shape and (3) the relative density. The first affects the mechanical, electrical and thermal properties, while the second, following the Maxwell criterion [
29], distinguishes bending-dominated structures from strength-dominated structures. The relative density is given by the ratio between the density of the cellular material (
ρ*) and the density of the bulk material (
ρs) [
24]. The relative density and the type of unit cell strongly affect both the cooling rate of the material during the solidification and the load distribution during its working conditions. High cooling rate values may lead to forming a microstructure mainly composed of α′ martensite, in contrast with the bulk material [
18,
25,
30‐
37]. Up to date, several studies have been focused on evaluating the performance of lattice structures. For instance, Del Guercio et al. [
38] have analysed the mechanical performance of three different types of lattice structures: (i) Dode thin, (ii) G-Structure 3 and (iii) Rombi-dodecahedron. The structures have been tested under compressive at room temperature in their work. According to Ashby and Gibson [
24], the results showed that three main trends characterize the stress-strain trend: (1) elastic behaviour of the lattice structures (a linear segment), (2) progressive collapse of the layers up to the point where (3) the structure has the same behaviour of the bulk material. The limit of the elastic behaviour is the failure point, namely, when the stress reaches the ultimate compressive strength (
UCS*), and the strain reaches the elongation at failure (
A*). Typically, the failure mode in these components is a brittle fracture at 45°, as reported in the literature [
36‐
42]. The lattice structures manufactured in larger cell sizes showed the worst mechanical performances, in terms of both Young’s modulus and
UCS*, with respect to those produced with smaller cell size [
38,
41,
43,
44]. Ashby and Gibson [
24] proposed a model to describe the mechanical performances of lattice structures, in which a generic relative property can be expressed, in a bi-logarithmic diagram, as a linear relationship of the lattice relative density. Thereafter, several studies have used Ashby and Gibson’s [
24] model to fit their evaluated mechanical properties experimentally. Additionally, Del Guercio et al. [
38] proved that the absorbed energy up to failure (
W*) also follows an Ashby-Gibson-like relationship. However, they also showed that the relative density is not totally descriptive of the mechanical behaviour of the lattice structure. All in all, several efforts have been made to evaluate the effect of cell type and cell size on the compressive behaviour of the EBM Ti-6Al-4V lattice structures. However, far too little attention has been paid to the effect of different heat treatments on the mechanical properties of the EBM lattice structures. This can potentially open new opportunities and widen the range of application of Ti-6Al-4V lattice structures. Several studies have shown the potential of the heat treatment on Ti-6Al-4V bulky parts. Several works proved that the overall porosity of the parts made by EBM could be reduced by applying a hot isostatic pressing (HIP) treatment that is generally conducted at 920 °C for 2 h [
34,
45‐
47]. Tammas-Williams et al. [
46] showed that the temperature in an annealing heat treatment enables the formation of new voids or pore regrowth during the heat treatment after HIP. De Formanoir et al. [
31] showed that thermal cycles significantly affect the mechanical response of the bulk parts. They studied two different heat treatments: the first was conducted below β-transus (transition temperature between the α and β phases is equal to 995 °C [
18]) at a specific temperature of 950 °C for 60 min. On the other hand, the second one was conducted at 1040 °C for a total time of 30 min. The results showed that at higher temperatures, the microstructure changed due to solid-state diffusion and coarsening of the plates of the α phase. As far as the response of lattice structure to heat treatment is concerned, far too little attention has been paid. As an example, Epasto et al. [
48] studied the compressive behaviour of Ti-6Al-4V cellular structures manufactured by EBM, which were heat-treated to reduce residual stress. They concluded that the possible presence of residual stresses does not significantly affect the compressive behaviour of Ti-6Al-4V lattice structures manufactured by the EBM process. On the other side, in a new approach on the design of the complex shape components, a mix of lattice and bulk structures is generally used in order to reduce their weight while keeping their mechanical performance as high as their fully bulk ones. Therefore, the aim of the present study is to deeply analyse the effect of different heat treatments on the lattice structures. With this scope, the microstructure and mechanical properties of the Ti-6Al-4V lattice structures produced by EBM process in the as-built and heat-treated states are compared. Isothermal heat treatments were performed below and above the β-transus. Compressive tests at the ambient temperature are conducted with the aim to correlate the mechanical performance to the microstructure variation induced by the heat treatments.