Research Article | Open Access
Repairing 2024 Aluminum Alloy via Electrospark Deposition Process: A Feasibility Study
The electrospark deposition (ESD) technique has been studied as a potential method to repair locally damaged 2024 rolled sheets supplied in natural-aged (T4) and artificial-aged (T6) conditions. The 2024-T4 and 2024-T6 tensile samples were first notched, and then the notches were filled (repaired) by ESD with the same aluminum alloy. The effect of process parameters on the microstructure of the filling material and the substrate properties was studied by optical and scanning electron microscopy. Tensile and hardness tests were performed. The tensile test showed that T4 and T6 as-repaired specimens had low tensile properties, which was due to defectiveness and residual stress caused by high cooling rate during reparation. However, the as-repaired specimens were heat-treated at either 135°C or 190°C to improve the mechanical properties. A better yield strength was observed for the T4 heat-treated alloy. The ductility and ultimate tensile strength did not change, being mainly affected by voids and microcracks.
The need to reduce operating, maintenance, and waste-related costs of an aircraft has prompted aeronautical industries to develop new repair procedures for aeronautical components. Besides, because of the extreme cost of materials and labor for fabricating high-value component, it is also necessary to repair all those components which are affected milling ball indentation and cutter pull out, which occur during the manufacturing process [1, 2]. New repairing technologies should overcome the limitations of the actual ones and be able to operate in the maintenance facility, which would avoid transporting it in a repairing workshop or sending the worn-out part to the original manufacturer .
Aluminum alloy 2024 was a forerunner of a variety of 2xxx series alloy that is widely applied in the aerospace industry for its superior properties such as high strength-to-weight ratio, very good resistance to fatigue crack growth, and good fracture toughness [4, 5]. It is commonly supplied in the T4 or T6 temper since such treatments give good mechanical properties. Generally, the 2024 parts used in aviation for damage tolerance applications, such as the lower wing skins and fuselage structure of commercial aircraft, usually easily undergo localized corrosion (i.e., pitting and exfoliation) especially in chloride-containing environment [6, 7].
Unfortunately, the conventional fusion welding methods (i.e., tungsten inert gas welding (TIG), plasma transferred arc and electron beam welding, and laser cladding) are not suitable for repairing this alloy [1, 5]. It has been proved that several problems like solidification cracking, grain boundary melting in the base metal (liquation cracking), and changes in metallurgical structure would arise mainly due to the high thermal process input [8–14].
Electrospark deposition (ESD) technology is an effective method for the deposition of anticorrosion and wear-resistance coatings. It is a low heat input pulsed microbonding process that uses high-energy density and short duration of electrical pulses, typically ranging from a few microseconds to milliseconds, to deposit the electrode material onto the component’s surface. It appears to be a very interesting and economic solution for the restoration and refurbishment of worn or damaged high-valued parts, especially those materials ordinarily considered poor-weldable by conventional repairing processes [2, 15–21].
In this technique, an electrical arc is pulsed between a rotating consumable electrode (anode) and the workpiece/substrate (cathode) to produce the deposit by detaching small droplets of material from the electrode and ejecting towards substrate. During the process, the electrical arc is pulsed with a frequency varying between 0.1 and 4 KHz using a high-frequency power supply [22, 23].
The short pulse duration and high-pulse frequency induce both very fast cooling rate and a rapid solidification process in combination with a small amount of material transferred during each pulse ESD technology. This rapid solidification rate, believed to approach 105-106°C/s, results in the refinement of the microstructure to either the nanostructured or amorphous level . The solidification mode of the deposited alloy, as well as the resulting grain morphology, is controlled mainly by the thermal condition that exists at the beginning of the solidification. Otherwise, the fine scale microstructure is controlled primarily by the postsolidification cooling rate .
This innovative technology has gained much interest in the repairing field since it can offer a variety of advantages including low pollution, technical feasibility for metal deposition in atmospheric pressure, and welding equipment handling and transportability. Moreover, the reduction of residual stress and distortion compared to the other fusion processes renders this technique highly applicable to those materials possessing a high tendency to crack during welding, such as superalloys, MCrAlY, and thermally sensitive materials (2000 series aluminum alloy) [22–24].
Many works have studied the mass transfer that occurs during the ESD process [25–27], which is paramount to produce a high wear-resistant coating [28–32]. The relationship between process parameters and the deposit structure has been also investigated [33–36]. Only few studies are related to the utilisation of ESD as a repair technology. Farhat  determined that the repair of a locally damaged NiCoCrAlY or CoNiCrAlY coating can be done by ESD to further extend the lifetime of coatings. While Johnson showed the possibility of repairing a single crystal turbine blade with low net heat input free from distortion .
Besides, to date investigations focused on assessment of ESD as repair technology, not concerning thermally sensitive materials such as the 2024 alloy.
In this paper, a comparative study between deposits prepared by ESD on AA2024 standard dog-bone substrates both in natural-aged (T4) and artificial-aged (T6) states has been presented. Detailed analyses of the microstructure modification of the filling alloy and the effect of process parameters on the substrate properties and microstructure were performed.
Furthermore, the as-repaired specimens were heat treated at 135°C and 190°C to reduce the detrimental effect of residual stresses on the mechanical properties. Hence, also the effect of postrepair heat treatment (PRHT) on the microstructure and mechanical properties of the repaired specimens was investigated.
2. Experimental Methods
AA2024 aluminum alloy was used for the electrode and the substrate materials. ESD substrate was supplied as T4 and T6 rolled plates. Chemical components (wt. %) of the AA2024 alloy are listed in Table 1.
Dog-bone specimens were realized from 4 mm thick plates (Figure 1(a)). A notch was machined in the midsize of the dog-bone specimens to be later filled up with the electrode material, as shown in Figure 1(b). Deposition was carried out using a hand-held gun at room temperature with argon (Ar) protection, which avoids contamination of the deposit zone by interstitial elements such as oxygen or nitrogen. During deposition, the electrode rotated at 1200 rpm speed. The electrospark deposition process parameters are shown in Table 2, where E is the value of the electric arc pulse energy in Joule. These parameters are based on a previous study of Leo et al. .
The substrate was kept in a fixed position, while the hand-held gun was moving according to three orthogonal XYZ axes. At the beginning, the semicircular shape of the notch was coated by adjacent depositions. The depositions had circular shape to fit the semicircular shape of the notch. The close semicircular depositions were realized to cover the entire surface of the notch along the y-axis. The filling was obtained by superimposing several depositions along the Z direction (Figure 1(b)). Then, the samples were postrepair heat treated (PRHT) for 2 h at 135°C and for 6 h at 190°C. All samples were air-cooled. Holding times and temperatures are displayed in Table 3. Samples were sectioned across the deposit center, embedded in epoxy resin and then polished to a mirror finish. Analyses were performed on the XZ section in the as-polished condition to assess the metallurgical health within the deposit and in the bonding zone. The microstructure was revealed by etching with Keller’s reagent. Three complementary methods were used to study the microstructure: stereo microscopy (SM), optical microscopy (OM), and scanning electron microscopy (SEM) with EDS. The grain structure of substrate was revealed by electropolishing (20% perchloric acid and 80% ethanol at 0°C; electropolishing parameter: 15 V and 60 s), anodic oxidation (Barker etching; anodizing parameters: 20 V and 80 s), and subsequent investigation under polarized light in OM.
The defect areas inside the deposit and the length of cracks at the substrate/deposit interface on the XZ plane (Figure 1(b)) were obtained using the NIS software for imaging analysis. NIS-Elements is a NIKON software supplied with Epiphot 200 OM. Defects area percentage was measured as the sum of the defect areas divided by the area of the repaired zone. Moreover, using ImageJ software, both Feret’s diameter and the shape factor (fcircle) of the filling defects have been evaluated. The shape factor comes from the following equation:where is the perimeter and is the area of defect. For a perfect spherical defect, the shape factor is one, while for a strongly elongated defect, it is very close to zero. Particularly, two main morphological classes of defects were considered in this study:(i)Defects with 0 < ≤ 0.5(ii)Defects with 0.5 < ≤ 1
Microhardness tests were performed with the load of 100 g for 15 s. Microhardness measurements were carried out on the XZ plane following a grid arrangement parallel to the top surface of the deposit in accordance with ISO 6507-1:2005. The distance between the indentations both in the horizontal and vertical direction was 100 µm. Then, the average values of microhardness were calculated considering all the indentation made in the deposit zone and in the BM, respectively. These measures were carried out on both as-repaired and PRHT samples. Tensile tests were carried out, at room temperature, in a universal testing machine in accordance with ISO 6892-1:2009 perpendicularly to the rolling direction (RD). The displacement control, at an initial strain rate of 0.25 mm/min, was used. Strains were measured with an axial extensometer with a gauge length of 12.5 mm.
3. Results and Discussion
3.1. Base Material Characterization
In AA2024-T4 alloy, the hardening mechanism is due to the Guinier–Preston zone (G–P zone) in the grains that hinder dislocation movement. While the AA2024-T6 reaches the peak hardness due to a finer transitional precipitates distribution that remains coherent with the solid-solution matrix, it contributes to precipitation strengthening. Both G–P zone (∼10 nm thick and 100 nm in diameter) and the precipitate particles (larger than G–P zone) are too small to be clearly resolved by OM or SEM microscopy [4, 5, 38]. Figure 2(a) presents the microstructure of the AA2024 alloy base material (BM) in the perpendicular direction to rolling manufacturing. OM and SEM micrographs of 2024, in T4 (Figure 2(a)) and T6 (Figure 2(b)) states, respectively, show the aluminum matrix together with a series of intermetallic particles of different morphologies and sizes. According to the literature and the SEM/EDS analysis, the main spherical intermetallic particles are Al2CuMg (S-phase) (1, Figures 2(a) and 2(b)), while the light grey particles are Al2Cu (θ phase) (2, in Figures 2(a) and 2(b)). Moreover, (Mn, Fe)3SiAl12 (light brown, 3, Figures 2(a) and 2(b)) and Al(Cu, Fe, Mn) phases (dark brown, 4, Figures 2(a) and 2(b)) were detected. They were as large as 10 m and had an irregular shape. Furthermore, according to the literature, the fine dispersoids in the Al matrix can be either Cu2Mn3Al20 or Al2Cu [5, 39]. The element mapping (Figure 3) of the BM confirmed the presence of those phases.
3.2. Defectiveness and Microstructure within the Fillings
Figures 4(a) and 4(b) show the SM pictures of the notch after filling with the ESD process. Figure 4(c) is an OM micrograph of a XZ plane of the electrospark filling. It can be clearly seen that the top surface was continuous and without visible cracks or other defects (Figures 4(a) and 4(b)). However, some defects are shown in Figure 4(c). The main defects detected in the analyzed fillings were voids with different morphologies and microcracks that extended both perpendicularly and parallel to the substrate/filling interface. In particular, the typical voids identified within the fillings had three geometries, that is, small spherical voids (gas porosity), large, random-shaped voids (bridging porosity), and thin void layer (laminar porosity) . The formation of these discontinuities depended strongly on the amount and localization of the fused material. During the manual deposition, the selected electrical parameters, the distance of the electrode to workpiece surface, and the force on the electrode did not remain constant during the deposition process [19, 36]. All the previous aspects changed the quantity of the metal that melted and/or evaporated. Therefore, peaks and valley formed on the surface, which appeared corrugated and showed voids [19, 30, 31]. Cracking within the filling is believed to be the result of the thermal stress, which builds up during cooling and solidification of the deposited material. The residual thermal stress in the filling was always tensile [40, 41]. Moreover, from the analysis of the substrate/filling interface, it was observed also that both the substrates in T4 and T6 states were characterized by cracks that preferentially extended along the grain boundaries (Figure 5(a)). High magnification SEM image outlined the crack path by the resolidified products, which are typical of the liquation cracking phenomenon (Figure 5(b)). Simultaneously, the rapid cooling from the ESD process induced a great thermal strain that opened the liquated zones. In fact, 2024 aluminum alloy is susceptible to solidification and liquation cracking having large range of solidification, high thermal expansion, large shrinkage, and many alloying elements [10, 41].
Optical and scanning electron micrographs on the XZ plane of the filling are shown in Figure 6. Numerous superimposed linear tracks can be observed clearly (Figures 6(b) and 6(c)) due to the remelting which was caused by the superimposed layer (layer-layer interface). Moreover, these layers differed in size and overlapped one over the other. The random size layers just revealed the instability in the manual deposition process. The average thickness of the several deposited layers was calculated through the application of intercept method. It was then determined to be ∼12.4 ± 6.1 µm. In addition, columnar grain structure grew perpendicularly to the substrate (Figures 6(a) and 6(b)). These columnar grains grew epitaxially along the crystallographic direction of previously solidified grain, through multiple layers, producing microstructure normal to the deposition layers [10, 36, 38, 42]. The coating microstructure was fine due to the high cooling rate [15, 16]. Moreover, some layers were characterized by a cellular dendritic microstructure (highlighted by the circle B in Figure 6(d)), and some other layers showed a uniform distribution of fine small second phase particles (appearing as light point in the circle A of Figure 6(d)). Moreover, the interlayer thin zone exhibited a coarse microstructure, generally equiaxed (highlighted by the box C in Figure 6(d)). These different microstructure morphologies in thin deposit layers can be attributed to the variable solidification conditions in the volume of the molten splat (liquid phase) [16, 43]. The interface between the filling and substrate is shown in Figure 7. The filling formed a metallurgical bound with the substrate (Figure 7).
3.3. Analysis of Defects
The defects in the filling material and at the filling/substrate interface were examined in detail. In the filling, for all the samples obtained, some randomly distributed defects with spherical and laminar shapes were observed in the deposit volume. The average area fraction of these defects was 2.5%, which can be considered acceptable. Figures 8(a) and 8(b) display the plots of the Feret diameter as a function of the shape factor and the percent distribution of the defects having shape factor between 0 and 0.5 and 0.5 and 1, respectively. As exhibited in Figure 8(a), the defects of larger size were the most irregular ones and the fillings were mainly characterized by laminar defects (shape factor included between 0 and 0.5). In fact, the Feret diameter distribution of the defects shown in Figure 8(b) illustrated how the almost totality of defects with between 0 and 0.5 had length shorter than 20 m. In addition, 50% of them had diameters between 10 m and 20 m, but with defects of considerable extension. The tensile thermal stress increased during the growth of the filling, causing large cracks in the filling and delamination at the weak interface bond. The small size voids were created by the formation of asperities or trapped gas. Figure 8(b) shows that spherical defects ( 0.5–1) were mostly distributed (90%) in the lower class of the Feret diameters (up to 10 m) while the remaining had Feret diameters between 10 and 30 m. Regarding the defects at the substrate/filling interface, for the two different treatment conditions of the BM (T4 and T6 states), the values of the average crack length and the ratio between the crack number and interface length (mm) examined are obtained and reported in Table 5. In addition, Figure 9 shows the distribution of the length of cracks that propagated in the substrate from the substrate/filling interface in the BM state T4 and T6. It is noteworthy that the ESD process generated the same /mm value regardless of the BM state (T4 or T6) and a considerable rise of the average crack length in the T6 BM. The increase in the average crack length observed in 2024-T6 sample was due to the high hardness of the substrate. Once triggered, the cracks propagated more easily thanks to the brittleness of the region. In fact, observing the crack length distribution plots, the deposition on the 2024-T6 sample produced lower crack percentage for length fields below 15 µm and a rise in the percentage of longer cracks with consequent rise in the crack length field variation. Therefore, the depositions made on the 2024-T6 induced greater defects at the interface than the depositions made on the 2024-T4.
3.4. Mechanical Characterization
Figure 10 shows the microhardness profiles of the fillings and AA2024 substrate both in T4 and T6 conditions. The graph shows the average microhardness values detected at increasing distances from the substrate/deposit interface. Table 6 shows the average microhardness. In addition, the average microhardness values of the substrate measured at 100 µm from the coating interface are indicated. The hardness of the filling was generally lower than that of the substrate in all the samples examined (Figure 10 and Table 6). The decrease of the hardness was due to the aging in the base material and to some defects, which formed inside the coating. Moreover (Figure 10), in the repaired zone, the average microhardness values remained almost constant, which confirm that there were no significant microstructural changes along the thickness of the repaired zone. The results in Table 6 suggest that the microhardness of the substrate close to the interface did not vary compared to that of the BM zone. Therefore, the mechanical properties of the substrate were not altered. Furthermore, the results showed that the postrepair heat treatment (PRHT) performed on samples had no effect on the hardness of the filling. In fact, it remained almost constant regardless of the heat treatment temperature employed. The hardness of 2024-T4 substrate, that was underaged, increased after the T190_6 PRHT due to the precipitation of more hardening particle . Due to overaging, the hardness value of the 2024-T6 substrate, that was peak aged, decreased with the increasing time and temperature of the heat treatment. In fact, it is known that if precipitate particles are large and widely spaced, they can be readily bypassed by moving dislocations which bow out between them and rejoin by a mechanism first proposed by Orowan .
3.4.2. Tensile Behavior
The tensile test was carried out to determine the behavior of the repaired specimens. Table 7 contains the values of the yield stress (σy), ultimate tensile strength (UTS), the load at fracture, strain at fracture (elongation ef), and cross-sectional area (S0) for as-received BM in T4 and T6 states, as-received BM notched, and repaired specimens both in untreated and treated T135_2 and T190_6 states. The stress-strain curves obtained are shown in Figure 11. From the results of the tensile tests, both as-repaired and PRHT samples displayed a decay of the mechanical properties compared BM (both notched and unnotched 2024 samples). This was probably caused by the presence of widespread defects inside the deposit and at the substrate/deposit interface as well as by different microstructural characteristics of the deposit and the BM. The yield stress (σy) and the ultimate tensile strength (UTS) of the as-repaired samples and PRHT samples were lower with respect to the notched samples. At the same time, a reduction in ductility owing to the defects present within the deposit and at the interface was observed. Porosity in the deposit led to stress concentration, so the crack easily started and propagated throughout the sample thickness. Moreover, the cracks at the interface induced the low tensile strength rupture. An increase of the mechanical properties (Table 7) was obtained by the high temperature and long duration PRHT treatment. The yield strength and UTS of the PRHT samples were greater with respect to the as-repaired samples. The T135_2 heat treatment increased the tensile strength of the 2024-T4 samples of 17 MPa and the yield strength of 34 MPa, while the T135_2 heat treatment increased the tensile strength of the 2024-T6 samples of 16 MPa and the yield strength of 39 MPa. Likewise, the T190_6 heat treatment increased the tensile strength of the 2024-T4 samples of 16 MPa and the yield strength of 72 MPa, while the T190_6 heat treatment increased the tensile strength of the 2024-T6 samples of 18 MPa and the yield strength of 46 MPa. The improvements of σy and UTS were primarily due to the reduction of the residual stresses and/or to the increasing of hardness due to heat treatment. The role of the residual stress reduction was particularly effective in the case of the PRHT performed at 190°C on the 2024-T6 sample in which the rise in the yield strength was associated with the overaging of precipitated particles (Table 6), which leads to softening of microstructure. So, the PRHT at 190°C was more effective when carried out on the 2024-T4 sample since, in addition to a residual stress reduction, the heat treatment also led to an increase of the substrate hardness.
The study of the 2024 aluminum alloy electrospark deposition process on a similar substrate brought the following evidences:(1)The filling microstructure was layer by layer, very fine, and mixed with both cellular and equiaxed dendrites. In the filling layers, grains formed long columnar grains with a preferential growth along the build-up direction. The microstructure was strongly inhomogeneous due to the different cooling rates during the deposition process. The hardness of the deposited metal was lower than that of the substrate. The substrate did not present a heat affected zone.(2)The reparation showed the presence of some defectiveness. Those defects, randomly distributed in the microstructure had spherical, casual, and laminar shapes. The average area fraction of these defects was 2.5% which is considered acceptable. It was estimated that the fillings had 63% of laminar and 37% spherical shape defects. The formation of defects with laminar morphology was mainly attributed to the tensile residual stresses. The length size of the cracks to interface was higher for the artificial aged deposition.(3)The tensile properties of the repaired samples were lower compared to the notched ones (for both T6 and T4 states) due to the residual stress and defectiveness. The PRHT improved the yield strength of the repaired specimen by reducing residual stress. However, the ductility of the 2024 alloy was strongly reduced by the reparation process. PRHT at 190°C was most effective when carried out on 2024-T4 since, in addition to a residual stress reduction, the heat treatment also led to a rise in the substrate hardness.
Conflicts of Interest
The authors declare that they have no conflicts of interest.
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