**1. Introduction**

The additive manufacturing market (AM) applied to the aerospace sector has experienced a big increase in the last decade. According to the report carried out by Wohlers Associates, the worldwide revenue from AM related services reached 6 billion dollars in 2016 and the forecast is to ge<sup>t</sup> to 21 billion by 2020 [1]. In fact, the first titanium 3D-printed part of the Airbus A350 XWB entered serial production after the approval of the European Union Aviation Safety Agency (EASA) in late 2017.

The most extended AM technologies (such as laser melting deposition (LMD) and selective laser melting (SLM)) are based on the fusion a metallic powder using a laser or an electron beam as a heating source. These processes can reach good dimensional accuracy, but the part size is limited by the low deposition rate (0.12–0.6 kg/h) [2]. To produce airframe parts of several meters economically, deposition rates of kilograms per hour are needed and this can be obtained by wire arc additive manufacturing (WAAM) [3].

WAAM uses a solid wire as the feedstock material and an electric arc as the heat source. Several research works have dealt with the fundamental aspects of the process such as the final material microstructure and its mechanical properties [4–7]. In this regard, the review recently presented

by Rodrigues et al. [8] provides an overview of the di fferent process variants and the materials for WAAM. Moreover, it also deals with the e ffect of the post-processing treatments in the final mechanical properties as well as with non-destructive testing.

Among the di fferent workpiece materials, titanium-based alloys are being increasingly tested in WAAM owing to their adoption by the aerospace industry for airframe manufacturing. For example, Ti alloys represent 15% of the weight of the Boeing 787 [9]. The microstructure and mechanical properties of Ti6Al4V alloy parts made by WAAM were investigated by Wang et al. [6]. Microstructural banding was observed, and it was related to the repeated thermal cycles that occur during the layer by layer growth of the workpiece. Regarding mechanical properties, the yield and ultimate tensile strengths were found to be lower in the WAAM part than in that produced by forging. However, similar ductility values were observed, and the mean fatigue life was significantly higher in the workpiece produced by WAAM. In a recent study, Ho et al. [4] investigated in grea<sup>t</sup> detail the microstructure banding found in this alloy using both multiscale compositional and automated image mapping tools. This approach provided evidence of weak micro-segregation during solidification and explained the origin of such microstructure.

The main disadvantages of WAAM, when compared with other AM processes, are the reduced dimensional accuracy and poor surface finish [10,11]. Therefore, a machining operation is mandatory to achieve the functional requirements. During the assembly of an airframe, for example, a large number of holes are machined, and the control of the drilling operation becomes crucial.

Drilling of titanium is one of the most complex processes in the production of aircraft structures. Ti alloys have been reported as di fficult to cut materials owing to their particular physical properties [12–14]. On the one hand, their low thermal conductivity (about 15 W/m K versus 270 W/m K for the steel CRS1018 at 700 ◦C) [15] leads to high temperatures in the cutting zone. However, they maintain their high mechanical strength and abrasiveness at such temperatures, resulting in high forces and fast tool wear. On the other hand, the chemical a ffinity with tool materials leads to a fast titanium adhesion to the cutting tool. The resulting built up edge (BUE) or chipping of the cutting edges often lead to poor surface finish of the inner surface of the hole (and, in the worst scenario, to premature failure of the cutting tool) [13].

The selection of the most appropriate cutting parameters (feed and cutting speed) is of vital importance for the success of the process. Previous studies have thoroughly analysed the e ffect of cutting parameter variation in the cutting forces and the resulting hole quality. Sharif et al. [14], for example, evaluated the performance of both uncoated and coated tungsten carbide drills at various cutting speeds. They observed that the average surface roughness value (Ra) decreased by approximately 20% by doubling the cutting speed. They also reported that uncoated drills are not suitable for cutting speeds over 25 m/min owing to their fast wear. In another study, Le Coz et al. [12] carried out a comprehensive study to test the e ffect of the variation of both the feed and cutting speed in the cutting forces. They observed an increase of a 60% in the cutting torque when the feed per revolution was increased in the same extent. This rise of cutting forces can be explained by the direct relationship between the feed and the cross-sectional area of the undeformed chip. The evolution of cutting forces was also investigated in the work of [14]. In this case, lower torque values were observed when increasing the cutting speed; this result was attributed to the reduction of the material hardness as the temperature increased.

The overall quality of the machined hole is also of grea<sup>t</sup> importance for the correct behaviour of the mechanical joint. Burr formation and poor geometrical quality, for example, can result in a reduction of fatigue life. Additional deburring or reaming operations are needed for the correction of such defects, and they generally imply a high cost [16]. Burr formation is dependent on various aspects such as tool geometry and material, workpiece material properties, and the selected machining parameters (among others) [17]. Apart from this defect, geometrical imperfection (such as irregular hole diameter) is also of critical concern. When drilling Ti alloys, the machined holes may shrink or expand depending on the cutting environment. Oversized holes are often obtained in dry cutting owing to the thermal expansion resulting from the high cutting temperatures. The influences of feed and cutting speed variation on hole diameter are complicated to study owing to their interacting effects [18]. Elastic recovery of compressive strain produced by thrust force may decrease the hole size. However, material expansion at high temperatures can lead to a hole larger than expected.

Despite extensive research work in Ti drilling, there are few works that have studied the machining of parts produced by AM. Priarone et al. [19] investigated the machinability of a gamma titanium aluminide obtained via the electron beam melting (EBM) process. In this work, drilling performance was measured in terms of surface roughness, dimensional errors, and tool wear. The experimental results showed a decrease of surface roughness when feed was decreased, as well as when the cutting speed increased. Hole quality also showed a dependence on the cutting parameters and tool wear level.

Even if WAAM could be a viable alternative to manufacturing aerostructure components, there is a lack of an experimental investigation on the drilling of titanium parts produced by this AM process. This work aims to reveal the influence of material properties by comparing the machining of commercial laminated plates to those produced by WAAM. In particular, the resulting chip morphology, cutting forces, and overall hole quality are analysed. For a deeper understanding of the cutting process, workpiece microstructure and mechanical properties are also studied. The novelty of this paper lies in the study of WAAM additive technology for the production of Ti6Al4V aeronautical titanium alloy parts and in experimentally addressing the drilling operation, as it is one of the most recurring machining operations in this type of applications.

## **2. Materials and Methods**

#### *2.1. WAAM Deposition Process and Material Analysis*

Linear wall parts were produced using an Addilan V0.1 wire arc additive manufacturing machine (Durango, Spain) and plasma arc welding (PAW) as addition technology with compressed argon as a pilot gas to prevent oxidation and porosity. This machine has a closed loop control system and an inert chamber to work under controlled Argon atmosphere to protect the melt pool when using reactive materials like titanium or aluminum, and can reach deposition rates up to 6 kg/h.

The experiments were carried out on a Ti6Al4V annealed base plate (AMS 4911 according to the AMS4928 standard), which had a dimensions of 220 mm × 70 mm × 12 mm. Prior to welding, the substrate surface was cleaned with acetone to remove any organic contaminants. A 1.14 mm diameter Ti6Al4V solid wire electrode (AWS A5.16-13 ERTI-5) was used for deposition and the chemical compositions of both the substrate and the wire are shown in Table 1.


**Table 1.** Nominal composition of welding wire and substrate.

The same deposition sequence was used for all the parts. First, the walls were obtained using a deposition rate of 2 kg/h and following the strategy shown Figure 1b. The pre-heating and inter-pass temperatures on the top layer were of 600 ◦C. Table 2 shows the welding parameters used for the sample processing. Finally, after the deposition was completed, the parts were stress relief treated by keeping them in a furnace at a temperature of 720 ◦C for 2.5 h.

**Figure 1.** (**a**) ADDILAN V0.1 wire arc additive manufacturing (WAAM) ([20]) and (**b**) schematic process sequence for wall manufacturing.



The determination of mechanical properties of the additively manufactured parts was obtained by tensile testing according to EN ISO 6892-1 standards. More specifically, the end start sections of the thin-walled structures were discarded and the samples for the tensile tests were prepared as shown in Figure 2. The tests were carried out at room temperature and with a speed of 1 mm/min, according ISO 6892-2, less than 5 Mpa/s in the elastic region. The chemical composition of the walls was also evaluated after the deposition process by infrared spectroscopy (IR spectrometry) for carbon C, oxygen O, and hydrogen H; thermal conductivity analysis for nitrate N; and optical emission spectroscopy (OES) for iron Fe, vanadium V, and aluminum Al.

Moreover, metallographic preparation was performed on samples sectioned along the XZ, XY, and YZ planes of the workpiece (see Figure 4), which were hot-mounted in a phenolic resin powder. Afterwards, they were subsequently polished using a series of abrasive grinding papers with decreasing coarseness from 1200 grit, followed by a final diamond suspension polishing. Finally, the samples were etched in Kroll's reagen<sup>t</sup> and optical images of the microstructure were obtained. Micro-hardness tests were also conducted in two samples of the walls produced by the WAAM process and in the laminated material used as reference for the machining tests. In order to carry out the measurements, an EMCOTEST DuraScan G5 (Kuchl, Austria) microhardness tester with a 10-kgf (98 N) load was used according to ISO 6507 procedures.

**Figure 2.** Dimensions of the samples for tensile tests in mm, Rz in μm, (**a**) and schematic representation of the location of the extracted samples (**b**).

#### *2.2. Experimental Setup for Drilling Tests*

The drilling trials were performed on a five-axis computer numerical control (CNC) machining center Ibarmia 5-axis ZV 65/U600 EXTREME (Azkoitia, Spain) and in collaboration with KENDU tools (Segura, Spain). WAAM specimens were rigidly clamped to the machine bed and the bottom and top faces were milled to produce a smooth surface for the final drilling operation. Figure 3 shows one of the parts after the WAAM process, during the milling operation and it final state before the drilling tests.

**Figure 3.** Additively manufactured part sample after the deposition process (**a**). Milling operation (**b**), part sample after milling process (**c**).

The drilling trials (Figure 4a) were performed using an uncoated ISO K30 KENDU tungsten carbide (WC) drill with diameter of 7.5 mm, a point angle of 140 mm, and a helix angle of 30◦. An overall view of the tools is shown in Figure 4b. Two sets of experiments were carried out in order to investigate the influence of the feed and cutting speed, respectively. The levels of machining parameters selected were based on the recommendations of the tool supplier and are detailed in Table 3. A peck drilling strategy and minimum quantity lubrication (MQL) cooling were used to enhance chip evacuation and to reduce cutting temperature. In order to study the dispersion of the process, three repetitions were carried out with the same drilling parameters. Furthermore, the holes were arranged in a grid pattern and were randomly located to consider sample variability.

As previously mentioned, one objective of this work is to compare the performance of the drilling process of WAAM parts to those produced by conventional methods. Thus, these drilling tests were repeated in a conventional titanium plate.

**Figure 4.** (**a**) General arrangemen<sup>t</sup> of the equipment used for the drilling tests. (**b**) Front and side view of the used tools.

**Table 3.** Cutting conditions for the drilling experiments.


During the drilling tests, thrust force and cutting torque were registered using a sensory SPIKE® toolholder (Pro-micron GmbH, Kaufbeuren, Germany) wirelessly connected to a PROMICRON READ acquisition system. Afterwards, cutting force signals were treated using the software MATLAB v2018a (Matworks, Massachusetts, Estados Unidos). As an example, Figure 5 shows the evolution of the thrust force for one peck drilling cycle in which three different stages can be identified. The first one (a–b) is related to the que tool entrance in the workpiece. In the second one (b–c), the cutting edge is fully engaged in titanium leading to a steady drilling process. Finally, the exit of the drill is produced at the last stage (c–d). The mean value of the steady drilling process stage (b–c) was considered for the comparison of the different drilling conditions and workpiece materials.

**Figure 5.** Thrust force evolution over time for a peck-drilling cycle.

After the drilling tests, hole quality was investigated by evaluating the diameter of the holes, their surface roughness, and the burr height at the hole exit. Hole diameter was measured at 6 mm from the tool entrance (i.e., the center of the inner surface) using a three-point internal digital micrometer (Mitutoyo Borematic® (Kawasaki, Japan) accuracy = 0.001 mm). Surface roughness was evaluated at the same hole depth using a Taylor Hobson Surtronik S100-series tester (Leicester, England) and the following filter values: λs = 2.5 μm and λc = 0.8 mm. Assessment of burr height was performed using a Leica DCM 3D confocal microscope (Wetzlar, Germany) at four equally-spaced positions around the hole periphery with an average calculation of the obtained data for each hole. Moreover, the overall chip geometry was also evaluated following the procedure proposed by Zhu et al. [21].

## **3. Results and Discussion**

#### *3.1. Mechanical Properties and Workpiece Microstructure Characterization*

In this section, the mechanical properties of the added material are analyzed in terms of the following: titanium alloy metallographic structure, mechanical results derived from the tensile test, hardness, and chemical composition of the material.

Figure 6 top left shows the titanium wall manufactured by means of WAAM technology from which the specimens were extracted, and grains' structure was observed. Macrographic pictures clearly show the interleaves of the deposition process of the di fferent beads as di ffusion occurs between passes. The microstructure of the wall at di fferent heights is shown, with the grain border and the dendritic structure derived from phases in which the temperature undergoes an abrupt decrease from the melting temperature necessary for the di fferent welds production. Owing to the influences of thermal gradient and solidification rate, the acicular α interwoven with a basket-weave structure and martensite α' the β matrix were generated.

**Figure 6.** Grain structure of the wall manufactured by plasma arc welding (PAW)-WAAM (**a**) at different heights and (**b**) from the top to bottom, as well as (**c**) micrographic pictures at different heights at 500X magnification.

The results of the tensile tests performed for the characterization of the walls are displayed in Table 4. The material was tested in the di fferent directions of the wall: vertical, horizontal, and oblique. The results are consistent, and it can be observed that the ultimate tensile stress and yield strength are slightly higher in the horizontal direction than in the vertical direction, with the oblique direction being the one with the highest results. This behaviour is the opposite of that observed in the elongation before the fracture, being the most critical parameter compared with the standard required for these materials in their aeronautical application.


**Table 4.** Mechanical properties: ultimate tensile stress (UTS), yield strength (YS), and elongation at break (Elong). PAW-WAAM, plasma arc welding wire arc additive manufacturing.

Table 5 shows the surface hardness at different depths of the WAAM titanium alloy wall. The mean values of microhardness are similar from top to bottom of the wall. An average value of 301 HV in the microhardness measured is measured at the wall. No differences are observed between the different depths. Regarding the values of chemical composition of the material, Table 6 contains the results obtained from the analysis of the wall. The values meet the requirements set by the standard that characterizes this titanium alloy (Ti6Al4V), which makes this technology very advantageous. The selection of the use of WAAM technology, plasma arc welding (PAW), under a controlled atmosphere of argon allows to ensure the stability of the material so that it does not vary its composition significantly with respect to the thread used as raw material in the process.


**Table 5.** Microhardness at different heights.



## *3.2. Chip Morphology Analysis*

Figure 7 shows the effect of cutting variables on chip morphology for the drilling tests of the specimen produced by additive manufacturing. As it can be noticed, the greater the feed, the smaller the chip length, while there is no big difference with the variation of cutting speed. This effect can be explained by the increase in the chip cross sectional area with the feed rate. A bigger cross-sectional area leads to a higher stiffness and, therefore, chips break more easily into segments. It is important to note that smaller chips are desirable in titanium drilling because a good chip extraction leads to lower thrust forces and cutting temperatures.

**Figure 7.** Effect of cutting speed and feed rate on chip morphology in drilling of WAAM specimen.

Moreover, as shown in Figure 8, it was also observed that, the higher the feed, and the smaller the cutting speed, and the greater the distance between two adjacent cones of the chip (geometrical parameter known as "pitch"). This effect also enhances chip breakability [21]. Similar results were obtained for the laminated specimen.

**Figure 8.** Effect of cutting speed and feed rate on the chip "pitch" (workpieces produced by WAAM).

To study in greater depth the chip formation process, a metallographic analysis of the chip cross section was carried out for some experiments. In particular, the part of the chip generated farther from the center of the tool was studied (see Figure 9). It should be noted that the cutting speed and rake angle are not the same in all the points of the cutting edge, leading to different material deformation and failure conditions.

Figure 9 shows the chip cross section for a workpiece produced by WAAM. A serrated chip formation process is noticeable with significant grain deformation in the primary shear zone. The appearance of such "shear bands" can be explained by a cycle of autocatalytic ruination [22]. During chip deformation, there is a local increase of the workpiece temperature produced by plastic work. During the short loading time, the temperature increases titanium's flow stress decreases and leads to an adiabatic shearing of the chip.

**Figure 9.** Metallographic analysis of the cross section of the chip for a workpiece produced by WAAM.

To compare the different machining conditions, two geometrical parameters were measured on the micrographs: the shear angle and the segmen<sup>t</sup> degree (see Figure 10). The segmen<sup>t</sup> degree of serrated chips is defined as G = (h1−h2)/h1 (h1 is the maximum teeth height and h2 is the minimum teeth height). For the drilling tests carried out in the workpieces produces by WAAM, a decrease in the shear angle with feed was observed for the tests with the same cutting speed. The bigger the feed, the higher would be the chip cross-sectional area and the plastic deformation level. As a consequence, workpiece temperature increases in shear zone and it becomes easier to slip. The segmen<sup>t</sup> degree shows an increase if a higher feed is used. For the studied machining parameter combinations, the results also showed that feed variation seems to have a bigger influence in the segmen<sup>t</sup> degree evolution than the change of the cutting speed.

**Figure 10.** Effect of the cutting parameters on the (**a**) shear angle and (**b**)segment degree for a workpiece produced by WAAM.

## *3.3. Cutting Force Magnitudes*

The knowledge of the evolution of cutting forces magnitudes with machining parameters is necessary for the process assessment. On the one hand, the machine-tool spindle should be able to generate enough torque for the cutting process. On the other hand, thrust force control is also important to minimize the vibrations of the drill along its axis as well as to reduce the bur height at the hole exit.

Figure 11 shows the effect of feed per tooth and cutting speed variation on the cutting torque value. An increase of cutting torque was observed when the feed per tooth was augmented. This result can be explained by the direct relationship between the cut chip thickness and the feed per tooth. Moreover, cutting torque decreased in both materials when the cutting speed was increased. The reduction of titanium's mechanical properties with temperature could explain this trend. These results are in accordance with the previous studies carried out in laminated titanium [13,15] and a

trends was observed for thrust force (see Figure 12). Finally, it should be noted that higher force values were obtained for the tests carried out in the titanium produced by WAAM as compared with those in the laminated material. The higher hardness (and overall better mechanical resistance) of the titanium produced by WAAM could be the reason for such a difference.

**Figure 11.** Effect of the cutting parameters and material manufacturing process on the cutting torque.
