Analysis of the Microstructure and Selected Properties of the Aluminium Alloys Used in Automotive Air-Conditioning Systems

The results of microstructure examinations and studies of selected mechanical properties of four aluminium alloys used in the production of automotive air-conditioning ducts (AA3103, AA5049, AA6060, AA6063) before and after the ASTM G85:A3 SWAAT Test (Sea Water Acetic Acid Test) for corrosion resistance are presented. Materials used for the manufacture of such components should be temperature stable, and therefore thermal resistance tests were carried out in a wide range of temperatures, i.e., −25 ◦C, 25 ◦C, 40 ◦C, 60 ◦C, 80 ◦C, 100 ◦C, 140 ◦C, 180 ◦C, and 220 ◦C. Annealing was performed for 72 h and 240 h, followed by cooling in water. The obtained results have proved that the non-precipitation-hardenable AA3103 and AA5049 alloys remain stable in the entire range of the investigated temperatures. The measured microhardness of these alloys was 43–46 HV0.1 for AA3103 and 56–64 HV0.1 for AA5049. The microhardness of the 6xxx series aluminium alloys was not stable in the investigated range of temperatures. The maximum was observed in the temperature range of 100–140 ◦C, which corresponded to the precipitation process of intermetallic phases, as further confirmed by microstructure observations. After the corrosion test, the mechanical properties and elongation decreased by about 5–20%.


Introduction
Aluminium alloys are widely used in various industries.One of their applications is the manufacture of components for heat exchangers in vehicles.The trend recently observed in modern car design is to reduce weight and obtain the maximum fuel economy.Consequently, various steps are taken to make the walls of components as thin as possible, while maintaining or even increasing the working pressure and operating temperature.Meeting such requirements is not an easy task, as it means there is a need to keep different properties that often exclude each other at an equally high level [1][2][3].Modern automotive heat exchangers operate at a temperature of about 100 • C and a pressure of up to 250 kPa (2.5 bars), but in heavy vehicles, the heat exchanger temperature can even reach 275 • C at a pressure of up to 350 kPa (3.5 bars) [1].
At present, the automotive industry uses the chemical agent R134a as a vehicle refrigerant, which belongs to the HFC group.This is, however, a transitional situation only, given that the EU Directives require its change in the near future for environmental reasons.
Agents such as hydrocarbons, R152a, and CO 2 have already found potential application as refrigerants in automotive air conditioning systems.It is believed that CO 2 (R744) has the greatest chance of being implemented, as it is non-flammable and environmentally friendly.However, its implementation will require a number of modifications to be introduced to the automotive air conditioning components [4][5][6][7].Air conditioners with R744 are operating under thermodynamically non-standard conditions.One of the major operational problems of CO 2 is the required high pressure of this medium.The working pressure parameters used for R744 are from 35 to 130 bars for low and high pressure, respectively, while the instantaneous values can occasionally even reach 160 bars.The temperature profile is also different, and at the outlet from the compressor, the temperature is nearly three times higher (about 160 • C) than the value obtained for the R134a agent.
When analyzing the properties of an automotive air conditioner, factors such as different operating conditions, including vibrations from the drive system, daily temperature changes, changes in the operating temperature, pressure, and environmental effects (e.g., the salinity of roads during winter, humidity), as well as the frequency of use, should be taken into consideration.
Under such, often extremely adverse, conditions, the use of aluminium alloys for parts of air conditioners is dictated by some favourable features of these alloys, such as their light weight, high strength, and corrosion resistance.The surface of aluminium alloys is immediately coated with an oxide film of about a 2-10 nm thickness.This thin film is stable in natural environments in the absence of chlorides and provides natural corrosion resistance to the metal.When the passive layer is damaged, a localized attack starts by the adsorption of aggressive anions and formation of soluble transitional complexes with cations at the oxide surface.Nominally, aluminium is passive in the pH range of ~4 to 9 due to the presence of an Al 2 O 3 film [8,9].
The corrosion potential of aluminium alloys depends on the composition of the aluminium-rich solid solution.The presence of intermetallic inclusions and changes in the chemical composition results in the formation of corrosive cells when water and brine are present, and due to this, the progressing corrosion can damage the surface of the air conditioner components.The most sensitive areas are those where individual parts are joined by brazing and where the occurrence of phase heterogeneity is unavoidable [9].Despite this fact, aluminium alloys are an excellent material for this type of application and hold an important place in the modern automotive industry.
Therefore, studies of aluminium alloys as a material for the air conditioning units using new refrigerants are of primary importance.The main aim of the research described in this paper was to determine the thermal stability, corrosion resistance, and mechanical properties of four aluminium alloys, i.e., 3103, 5049, 6063, and 6060, used in the manufacture of automotive air-conditioning components, and to investigate their suitability for operation with new agents.

Materials and Methods
Studies were carried out on four aluminium alloys of the chemical composition given in Table 1.The tested alloys were delivered in the form of 18 mm diameter tubes with a wall thickness of 1.5 mm, tempered to the following conditions: AA3103-H12, AA5049-F18, AA6060, and AA6063-T1.The samples were annealed at −25    C and 220 • C for 72 h and 240 h and then water cooled.Samples taken from the tubes were subjected to the ASTM G85 Annex 3 (A3) SWAAT test (Sea Water Acetic Acid Test).This is a corrosion test that uses synthetic sea salt instead of traditional sodium chloride.The solution is then acidified using glacial acetic acid.The test is to be operated under wet bottom conditions.Salt Solution: A synthetic sea salt solution made with the addition of glacial acetic acid, pH range: 2.8-3.0.The temperature of the saturator tower (bubble tower) was kept at 50 ± 1 • C. ASTM G85 Annex 3 (A3) SWAAT (ASTM International, Montgomery, PA, USA) utilizes the following cycle: 30 min spray followed by a 90 min soak at above 98% relative humidity.This test can be used to determine time to perforation primarily on aluminium alloy brazing sheets used for the manufacture of heat exchangers, or even on complete heat exchangers under pressure, or on other parts.It is also applicable in studies of the effect of varying heat treatment conditions on the corrosion behaviour.
Samples in the initial state and after annealing were examined with an Olympus GX51 optical microscope (Olympus, Tokyo, Japan) and Schottky electron gun Scanning Electron Microscope (SEM) (Hitachi, Tokyo, Japan) with Thermo Scientific NORAN System 7 X-ray microanalysis system (EDS)-Hitachi SU70 (Thermo Fisher Scientific, Waltham, MA, USA).Samples for microstructure examinations were mechanically ground and polished with diamond paste and a colloidal suspension of SiO 2 .The microstructure was revealed by the technique of etching with Barker reagent.The composition of the Barker reagent was as follows: 1.8 cm 3 HBF 4 + 100 mL H 2 O.The microstructure was additionally examined by transmission electron microscopy (TEM) using a JEOL 2010 ARP microscope (Jeol Ltd., Tokyo, Japan) with OXFORD Pentafet EDS Energy Dispersive Spectroscopy (Oxford Instruments, Abingdon, UK).The thin foils for electron transmission observations were cut out from the sample longitudinal sections and prepared by the standard technique of electrolytic polishing using Struers apparatus.Tubes after the corrosion test were also examined under an Olympus LEXT OLS 4100 confocal microscope (Olympus, Tokyo, Japan), additionally measuring the corrosion scale thickness.Information about the chemical composition and phase composition of samples was provided by the EDS and X-ray diffraction (XRD) analyses (PAN alytical Empyrean diffractometer (PANalytical, Almelo, The Netherlands), Cu Kα1 = 1.5417Å radiation, U = 40 kV, I = 30 mA, PIXel detector).
Vickers microhardness (HV) was measured on mirror-shine polished sample surfaces using a standard SHIMADZU HMV-2T E microhardness tester (Shimadzu Corp., Kioto, Japan) with a Vickers indenter.A load of 100 g was applied in the hardness measurements.
The tensile test was performed at room temperature on a Zwick Roell Z050 testing machine (Zwick Roell Group, Ulm, Germany) with a constant crosshead velocity corresponding to an initial strain rate of 10 −3 s −1 .In each case, the length of both the measuring base and mandrels was calculated based on the PN-EN ISO 6892-1: 2010 Standard.For each variant of the tube before and after the corrosion test, at least three samples were tested (24 samples in total).Based on the obtained results, the 0.2% yield strength (σ 0.2 ), ultimate tensile strength (σ UTS ), and elongation to failure (ε f ) were determined.

Microstructure Investigations
The characteristic microstructures and the phase analysis of the investigated alloys are shown in Figures 1-8.Additionally, Figure 1b, Figures 2-4, and Figure 5b show the results of point analysis.All tested alloys have a regular shape of grains, with a mean grain diameter of 20 µm for AA3103 and AA5049, 35 µm for AA6063, and 70 µm for AA6060.
For a more accurate determination of the chemical composition of the precipitates, an X-ray phase analysis was also performed.The peaks visible on the diffraction pattern indicate that in the 3103 and 5049 alloys, the precipitates are Al11Mn4.6 and Al6Fe0.5Mn0.5 phases.Additionally, two other phases were identified, i.e., Al9Fe0.84Mn2.16Si in the 3103 alloy and Al17.1Fe3.2Mn0.8Si1.9 in the 5049 alloy (Figures 6 and 7).In the 6xxx series alloys examinations by the X-ray phase analysis indicated the presence of peaks originating from the Al3Fe, Mg2Si, and Al5.15Mg3.15phases (Figure 8).For a more accurate determination of the chemical composition of the precipitates, an X-ray phase analysis was also performed.The peaks visible on the diffraction pattern indicate that in the 3103 and 5049 alloys, the precipitates are Al11Mn4.6 and Al6Fe0.5Mn0.5 phases.Additionally, two other phases were identified, i.e., Al9Fe0.84Mn2.16Si in the 3103 alloy and Al17.1Fe3.2Mn0.8Si1.9 in the 5049 alloy (Figures 6 and 7).In the 6xxx series alloys examinations by the X-ray phase analysis indicated the presence of peaks originating from the Al3Fe, Mg2Si, and Al5.15Mg3.15phases (Figure 8).For a more accurate determination of the chemical composition of the precipitates, an X-ray phase analysis was also performed.The peaks visible on the diffraction pattern indicate that in the 3103 and 5049 alloys, the precipitates are Al11Mn4.6 and Al6Fe0.5Mn0.5 phases.Additionally, two other phases were identified, i.e., Al9Fe0.84Mn2.16Si in the 3103 alloy and Al17.1Fe3.2Mn0.8Si1.9 in the 5049 alloy (Figures 6 and 7).In the 6xxx series alloys examinations by the X-ray phase analysis indicated the presence of peaks originating from the Al3Fe, Mg2Si, and Al5.15Mg3.15phases (Figure 8).

Thermal Stability Investigations
Due to variations in the operating temperature, materials used for the automotive air conditioning components should meet the condition of thermal stability.To confirm that all tested alloys meet this condition, annealing of tubes was carried out in a wide range of temperatures, i.e., from −25 °C to 220 °C, for the time of 72 h and 240 h, followed by hardness measurements.The obtained results are graphically depicted in Figure 9a-d  In the microstructure of all tested alloys, numerous evenly spaced precipitates of the size from a few nanometres up to several of microns were observed.The precipitates were most numerous in the 3103 alloy (Figure 1).Studies of the chemical composition in microregions carried out by EDS showed that in both alloys, i.e., 3103 and 5049, the precipitates were rich in Mn and Fe.On the other hand, TEM analysis of the chemical composition of these precipitates has proved that some of them contained silicon.In microscopic images, the silicon-containing precipitates were visible as dark grey particles, while the silicon-free precipitates had a bright colour (Figures 1b, 2, 3b and 4).In the microstructure of the 6060 and 6063 alloys, iron-rich phases (bright-colour precipitates) and magnesium-rich phases were present.Magnesium was also traced in the alloy matrix (Figure 5).
For a more accurate determination of the chemical composition of the precipitates, an X-ray phase analysis was also performed.The peaks visible on the diffraction pattern indicate that in the 3103 and 5049 alloys, the precipitates are Al 11 Mn 4.6 and Al 6 Fe 0.5 Mn 0.5 phases.Additionally, two other phases were identified, i.e., Al 9 Fe 0.84 Mn 2.16 Si in the 3103 alloy and Al 17.1 Fe 3.2 Mn 0.8 Si 1.9 in the 5049 alloy (Figures 6 and 7).In the 6xxx series alloys examinations by the X-ray phase analysis indicated the presence of peaks originating from the Al 3 Fe, Mg 2 Si, and Al 5.15 Mg 3.15 phases (Figure 8).

Thermal Stability Investigations
Due to variations in the operating temperature, materials used for the automotive air conditioning components should meet the condition of thermal stability.To confirm that all tested alloys meet this condition, annealing of tubes was carried out in a wide range of temperatures, i.e., from −25 • C to

Thermal Stability Investigations
Due to variations in the operating temperature, materials used for the automotive air conditioning components should meet the condition of thermal stability.To confirm that all tested alloys meet this condition, annealing of tubes was carried out in a wide range of temperatures, i.e., from −25 °C to 220 °C, for the time of 72 h and 240 h, followed by hardness measurements.The obtained results are graphically depicted in Figure 9a-d  The results of microhardness measurements have proved that 3103 and 5049 aluminium alloys are stable within the entire range of the heat treatment temperatures.The average hardness of 3103 and 5049 is 45 HV0.1 and 60 HV0.1, respectively.The differences are within the range of measurement error.A longer annealing time has nearly no effect on the level of microhardness (Figure 9a,b).
The situation was different in the case of 6060 and 6063 alloys, where changes in microhardness were found to be dependent on the annealing temperature.The microhardness of the 6060 alloy remained at a constant level of 59-64 HV0.1 up to a temperature of 80 • C. Annealing at higher temperatures resulted in its increase, followed by a decrease to approximately 46HV0.1 after annealing for 72 h and to 40 HV0.1 after annealing for 240 h.In the case of 72 h annealing, the microhardness peak occurred at 140 • C and the measured value of microhardness was 80 HV0.1, while after annealing for 240 h, the peak occurred at 100 • C with a microhardness value of about 90 HV0.1 (Figure 9c).
The microhardness of the 6063 alloy was higher than that of the 6060 alloy, and this was mainly due to the higher content of alloying additives and smaller grain size.When heat treated for 72 h, this alloy was stable up to a temperature of 140 • C (the average hardness was 80HV0.1),and then a decrease in hardness occurred.With the annealing time extended to 240 h, the microhardness started growing at 100 • C (92 HV0.1) (Figure 9d).Differences in the hardness of 6xxx series alloys are controlled by the precipitation process.In the 6xxx series containing magnesium and silicon, alloy properties are mainly shaped by the process of precipitation hardening, the result of which depends on the conditions of solution treatment and ageing.In the initial stage of the annealing process, separate clusters of Mg and Si atoms are formed in the solid solution.Then, joint clusters of Mg/Si appear, accompanied by the formation of GP zones [10][11][12][13][14]. AlMgSi alloys are most effectively strengthened by the β" phase of the Mg 5 Si 6 formula [10,15].During further ageing, the β phase is formed along with other phases which need a higher ageing temperature for their formation (200-300 • C) and are generally described in the literature as U2, U1, and B , or B, A, and C, respectively [10].According to the literature, several of the above-mentioned phases, e.g., β , U2, U1, and B , or β", β , U1, and U2 [10,12], can occur simultaneously in the microstructure of the aged alloys.In the final stage of ageing, the β-Mg 2 Si equilibrium phase is formed, while in alloys with a higher silicon content, silicon precipitates also appear.
Except for the β-Mg 2 Si phase, other phases are considered metastable during ageing treatment.The type of precipitates and their relative quantity depend on the alloy composition, mechanical deformation, and thermal history prior to ageing, e.g., the storage time at room temperature [10,16,17].Table 2 gives an overview of phases most commonly found in the AlMgSi system.It can be presumed that the growth peak observed in the microhardness graph is related to the occurrence of β″ phase precipitates in the microstructure of the alloys.The precipitates of this phase have the shape of needles of the maximum length of a few dozen nanometres and they are coherent with the crystal lattice only in their length [10].A higher annealing temperature results in a significant decrease of microhardness, overageing of the alloy, and precipitation in its microstructure of the β′ phase and of other phases defined as U2, U1, and B′.A detailed analysis of the dislocation microstructure may indicate that these are the precipitates of the β′, U2, and U1 phases.According to literature data, these precipitates have the shape of rods of up to a 500 nm length and form phases semi-coherent with the matrix [10].In the microstructure of the alloy in the initial condition, dislocation tangles and small precipitates are visible.

Corrosion Resistance Investigations
On the surface of tubes before corrosion tests, surface defects such as scratches and even micro cracks are visible (Figures 12a, 13a, 14a and 15a).Under favourable conditions, these defects can facilitate the development of corrosion process.Observations of the surface of tubes after the salt spray test show large variations in the morphology of the formed scale (Figures 12-15).In the 3103 and 5049 alloys, the scale forms "islands" and does not completely cover the surface of the tubes It can be presumed that the growth peak observed in the microhardness graph is related to the occurrence of β" phase precipitates in the microstructure of the alloys.The precipitates of this phase have the shape of needles of the maximum length of a few dozen nanometres and they are coherent with the crystal lattice only in their length [10].A higher annealing temperature results in a significant decrease of microhardness, overageing of the alloy, and precipitation in its microstructure of the β phase and of other phases defined as U2, U1, and B .A detailed analysis of the dislocation microstructure may indicate that these are the precipitates of the β , U2, and U1 phases.According to literature data, these precipitates have the shape of rods of up to a 500 nm length and form phases semi-coherent with the matrix [10].In the microstructure of the alloy in the initial condition, dislocation tangles and small precipitates are visible.

Corrosion Resistance Investigations
On the surface of tubes before corrosion tests, surface defects such as scratches and even micro cracks are visible (Figures 12a, 13a, 14a and 15a).Under favourable conditions, these defects can facilitate the development of corrosion process.Observations of the surface of tubes after the salt spray test show large variations in the morphology of the formed scale (Figures 12-15).In the 3103 and 5049 alloys, the scale forms "islands" and does not completely cover the surface of the tubes (Figure 12b,c and Figure 13b,c).On the other hand, it forms a thick layer on the surface of tubes made from the 6xxx series alloys, especially as regards tubes made from the 6063 alloy (Figures 14 and 15).Additionally, numerous cracks appear in the scale (Figures 14b and 15b).Their presence can facilitate the formation of corrosion centres and, consequently, accelerate the destruction of corrosion-affected installations under varying atmospheric conditions.etchout, intergranular attack, and exfoliation corrosion, is associated with the electrochemical nature of the intermetalic phases.Surface and subsurface grain etchout is also influenced by grain energy, which is directly related to the density of grain defects.The corrosion behaviour is often correlated with the difference of potential between the intermetalic compounds present in the alloy and the matrix.The mere existence of intermetallic compounds can promote failures in the protective oxide film [9,[18][19][20].other forms of localized corrosion, such as selective dissolution, trenching, intermetallic particle etchout, intergranular attack, and exfoliation corrosion, is associated with the electrochemical nature of the intermetalic phases.Surface and subsurface grain etchout is also influenced by grain energy, which is directly related to the density of grain defects.The corrosion behaviour is often correlated with the difference of potential between the intermetalic compounds present in the alloy and the matrix.The mere existence of intermetallic compounds can promote failures in the protective oxide film [9,[18][19][20].corrosion, best seen in Figure 15b.The susceptibility of aluminium alloys to pitting corrosion and other forms of localized corrosion, such as selective dissolution, trenching, intermetallic particle etchout, intergranular attack, and exfoliation corrosion, is associated with the electrochemical nature of the intermetalic phases.Surface and subsurface grain etchout is also influenced by grain energy, which is directly related to the density of grain defects.The corrosion behaviour is often correlated with the difference of potential between the intermetalic compounds present in the alloy and the matrix.The mere existence of intermetallic compounds can promote failures in the protective oxide film [9,[18][19][20].The corrosion process in aluminium alloys is generally of a local nature, because anodic and cathodic reactions are well-separated and solution resistance limits the galvanic cell size [9].In [18,21], the authors have demonstrated that when an aluminium alloy is exposed to the effect of NaCl solution, the corrosion of metal is accompanied by the oxidation of aluminium taking place as an anodic reaction: Since the solution of NaCl contains a certain amount of dissolved oxygen, the main cathodic reaction at the cathodic sites (outside the pits) will be the reduction of oxygen: attack, and exfoliation corrosion, is associated with the electrochemical nature of the intermetalic phases.Surface and subsurface grain etchout is also influenced by grain energy, which is directly related to the density of grain defects.The corrosion behaviour is often correlated with the difference of potential between the intermetalic compounds present in the alloy and the matrix.The mere existence of intermetallic compounds can promote failures in the protective oxide film [9,[18][19][20].
The corrosion process in aluminium alloys is generally of a local nature, because anodic and cathodic reactions are well-separated and solution resistance limits the galvanic cell size [9].In [18,21], the authors have demonstrated that when an aluminium alloy is exposed to the effect of NaCl solution, the corrosion of metal is accompanied by the oxidation of aluminium taking place as an anodic reaction: Since the solution of NaCl contains a certain amount of dissolved oxygen, the main cathodic reaction at the cathodic sites (outside the pits) will be the reduction of oxygen: or hydrogen reduction in acidified solution, such as occurs in a pit environment, as a result of aluminium hydrolysis: As a result of the cathodic reaction, the concentration of hydroxide ions increases, so the local pH becomes more alkaline and the following reaction occurs: Al(OH) 3 is further transformed into Al 2 O 3 by: Chloride ions from the corrosive atmosphere can react with the Al 3+ cations and form aluminium chloride.The possible corrosion products consist of Al(OH) 3 , Al 2 O 3 , and AlCl 3 [22].Figure 16 shows the microstructure of the AA6063 alloy and maps of the distribution of selected elements on the surface of the tube subjected to corrosion testing.Studies have confirmed the occurrence of the previously mentioned corrosion products.The corrosion process in aluminium alloys is generally of a local nature, because anodic and cathodic reactions are well-separated and solution resistance limits the galvanic cell size [9].In [18,21], the authors have demonstrated that when an aluminium alloy is exposed to the effect of NaCl solution, the corrosion of metal is accompanied by the oxidation of aluminium taking place as an anodic reaction: Since the solution of NaCl contains a certain amount of dissolved oxygen, the main cathodic reaction at the cathodic sites (outside the pits) will be the reduction of oxygen: or hydrogen reduction in acidified solution, such as occurs in a pit environment, as a result of aluminium hydrolysis: As a result of the cathodic reaction, the concentration of hydroxide ions increases, so the local pH becomes more alkaline and the following reaction occurs: Al(OH)3 is further transformed into Al2O3 by: Chloride ions from the corrosive atmosphere can react with the Al 3+ cations and form aluminium chloride.The possible corrosion products consist of Al(OH)3, Al2O3, and AlCl3 [22].Figure 16 shows the microstructure of the AA6063 alloy and maps of the distribution of selected elements on the surface of the tube subjected to corrosion testing.Studies have confirmed the occurrence of the previously mentioned corrosion products.
The measured thickness of the scale formed on the test tubes during the salt spray corrosion test depended on the alloy grade.The thickness of the scale formed on the 3103, 5049, and 6060 alloys was comparable and measured approximately 7.5-9 μm.Studies have shown that the thickest layer of scale was formed on the 6063 alloy; its average thickness was 17 μm (Figure 17).The measured thickness of the scale formed on the test tubes during the salt spray corrosion test depended on the alloy grade.The thickness of the scale formed on the 3103, 5049, and 6060 alloys was comparable and measured approximately 7.5-9 µm.Studies have shown that the thickest layer of scale was formed on the 6063 alloy; its average thickness was 17 µm (Figure 17).To identify the possible impact of a corrosive environment on the destruction of materials in the subsurface layer, cross sections of the tubes were examined.The results showed that in each case, the subsurface layer was destroyed, but the depth of changes penetrating into the material depended on the alloy grade (Figure 18).The AA3103 alloy was characterized by the highest resistance to the effect of a corrosive environment, while AA6060, where pitting locally penetrated into the material even to a depth of 300 μm, was the most corrosion-sensitive.The images in Figure 18 show the presence of local intercrystalline corrosion, which is particularly evident in the AA5049 and AA6060 alloys.This type of corrosion is extremely dangerous, as it can contribute to the formation of cracks, especially under the conditions of variable stresses and temperatures, to the extent that the automotive air conditioning components are exposed.The progressing corrosive changes contribute to the deterioration of mechanical properties, as confirmed by the results shown in Figure 19.To identify the possible impact of a corrosive environment on the destruction of materials in the subsurface layer, cross sections of the tubes were examined.The results showed that in each case, the subsurface layer was destroyed, but the depth of changes penetrating into the material depended on the alloy grade (Figure 18).The AA3103 alloy was characterized by the highest resistance to the effect of a corrosive environment, while AA6060, where pitting locally penetrated into the material even to a depth of 300 µm, was the most corrosion-sensitive.The images in Figure 18 show the presence of local intercrystalline corrosion, which is particularly evident in the AA5049 and AA6060 alloys.This type of corrosion is extremely dangerous, as it can contribute to the formation of cracks, especially under the conditions of variable stresses and temperatures, to the extent that the automotive air conditioning components are exposed.The progressing corrosive changes contribute to the deterioration of mechanical properties, as confirmed by the results shown in Figure 19.To identify the possible impact of a corrosive environment on the destruction of materials in the subsurface layer, cross sections of the tubes were examined.The results showed that in each case, the subsurface layer was destroyed, but the depth of changes penetrating into the material depended on the alloy grade (Figure 18).The AA3103 alloy was characterized by the highest resistance to the effect of a corrosive environment, while AA6060, where pitting locally penetrated into the material even to a depth of 300 μm, was the most corrosion-sensitive.The images in Figure 18 show the presence of local intercrystalline corrosion, which is particularly evident in the AA5049 and AA6060 alloys.This type of corrosion is extremely dangerous, as it can contribute to the formation of cracks, especially under the conditions of variable stresses and temperatures, to the extent that the automotive air conditioning components are exposed.The progressing corrosive changes contribute to the deterioration of mechanical properties, as confirmed by the results shown in Figure 19.respectively.As regards AA6060 and AA6063, neither of them is stable in the investigated range of temperatures.The maximum HV0.1 occurs in the temperature range of 100-140 • C and is due to the precipitation process of the intermetallic phases.

2.
Pitting is the main corrosion process.It starts in or around the intermetallic particles present in the alloys and is the result of the difference of potential between the intermetallic phases and the matrix.

3.
The obtained results have demonstrated a decrease in the mechanical properties and elongation of about 5-20%, observed in all the examined alloys after the corrosion resistance test in a salt spray chamber.This is mainly due to the effect of corrosion that attacks the material and penetrates into its interior.4.
Despite the adverse impact of corrosion deteriorating the strength properties of the tested alloys, the values obtained remain within the acceptable range.Hence the conclusion follows that all the tested alloys satisfy the imposed requirements and can be safely used for parts of the automotive air conditioning systems.

Figure 4 .
Figure 4. Microstructure and chemical analysis of precipitates in AA5049 alloy; TEM.
Metals 2018, 8, 10 7 of 15 220 • C, for the time of 72 h and 240 h, followed by hardness measurements.The obtained results are graphically depicted in Figure 9a-d.

Figures 10 and 11 14 Figure 10 .
Figures 10 and 11 show selected TEM images of the microstructure of 6060 and 6063 alloys in the initial state and after annealing at 140 • C and 220 • C for three days.Metals 2018, 8, 10 8 of 14

Figure 10 .
Figure 10.Microstructure of AA6060 alloy in the initial state and after annealing at 140 °C and 220 °C; TEM.Figure 10.Microstructure of AA6060 alloy in the initial state and after annealing at 140 • C and 220 • C; TEM.

Figure 10 .
Figure 10.Microstructure of AA6060 alloy in the initial state and after annealing at 140 °C and 220 °C; TEM.

Figure 11 .
Figure 11.Microstructure of AA6063 alloy in the initial state and after annealing at 140 °C and 220 °C; TEM.

Figure 11 .
Figure 11.Microstructure of AA6063 alloy in the initial state and after annealing at 140 • C and 220 • C; TEM.

Metals 2018, 8 , 10 11 of 14 Figure 16 .
Figure 16.Microstructure and maps of the Al, O, Na, Cl, Fe, Si, and Mg distribution on the surface of tube made from the AA6063 alloy after corrosion test; SEM.

Figure 16 .
Figure 16.Microstructure and maps of the Al, O, Na, Cl, Fe, Si, and Mg distribution on the surface of tube made from the AA6063 alloy after corrosion test; SEM.

Metals 2018, 8 , 10 11 of 14 Figure 16 .
Figure 16.Microstructure and maps of the Al, O, Na, Cl, Fe, Si, and Mg distribution on the surface of tube made from the AA6063 alloy after corrosion test; SEM.

Figure 16 .
Figure 16.Microstructure and maps of the Al, O, Na, Cl, Fe, Si, and Mg distribution on the surface of tube made from the AA6063 alloy after corrosion test; SEM.

Table 1 .
Chemical composition of the investigated alloys, wt %.