- Original Article
- Open Access
High cycle fatigue and fatigue crack propagation behaviors of β-annealed Ti-6Al-4V alloy
International Journal of Mechanical and Materials Engineering volume 12, Article number: 1 (2017)
The effect of β annealing on high cycle fatigue (HCF) and fatigue crack propagation (FCP) behaviors of Ti64 alloy were examined, and the results were compared to those of mill-annealed counterpart.
The tensile tests, stress-controlled HCF tests, and FCP tests were conducted, and the fractographic and micrographic analyses were performed before and after the tests.
The β-annealed Ti64 specimen showed inferior HCF properties as compared to the mill-annealed counterpart, as a result of lower yield strength. On the other hand the resistance to FCP of β-annealed Ti64 specimen was higher than that of mill-annealed counterpart in low and intermediate ΔK regime.
Relatively easy fatigue crack initiation at the colony boundaries of β-annealed Ti64 specimen reduce the resistance to HCF. The resistance to FCP of β-annealed Ti64 specimen increased significantly particularly in low ΔK regime along with severe crack branching and deflection.
Today’s high performance aircrafts, including engine power to weight ratios, airframe strength, aircraft speed and range, are largely attributable to the use of titanium alloys with high specific strength and fracture toughness (Ezugwu and Wang 1997; Andrade et al. 2010). The use of titanium alloys in airframe application has recently been growing as the use of CFRP (carbon fiber reinforced polymer) increases (Inagaki et al. 2014; Mrazova 2013). It is because designing joints between heterogeneous materials in an airframe must consider the prevention of galvanic corrosion and the elimination of strain caused by the difference in thermal expansion coefficients (Kaminaka et al. 2014; Donachie 2000).
A number of literatures have demonstrated that different heat treatment routes can produce a variety of microstructures in α + β Ti-6Al-4 V (Ti64) alloys, which strongly affects the static and dynamic properties (Venkatesh et al. 2009; Morita et al. 2005; Semiatin et al. 2003; Ivasishin et al. 2002; Chandler 1996). Typical heat treatment processes of Ti64 alloy are conducted in α + β region below β transus, including duplex annealing, solution heat treatment and aging (STA), recrystallization annealing, and mill annealing. Unlike the α + β processing, the β annealing of α + β Ti64 alloy is a less common type of hot working (Chandler 1996; Campbell 2011). The purpose of β annealing is to induce the microstructure of Widmanstatten or acicular α phase to obtain enhanced resistance to fracture, fatigue, and creep, albeit moderately sacrificing strength and ductility as compared to the microstructure of equiaxed α phase (Campbell 2011; Welsch et al. 1993; Wanhill and Barter 2011; Yoder et al. 1976). The β annealing is done at a temperature only slightly higher than the β transus to prevent excessive grain growth (Ivasishin et al. 2002). Annealing time depends on section thickness and should be long enough to permit complete transformation to β phase, while it should also be held to a minimum to suppress the grain growth of β phase (Donachie 2000; Ivasishin et al. 2002; Davis 1995; Borisova et al. 1975). The β annealing can be followed by passive air cool, although larger sections may need to be fan cooled or even water quenched to prevent the formation of detrimental layer of α phase at grain boundaries (Donachie 2000). In α + β titanium alloys, thermal instability is a function of β phase transformation since, cooling from the annealing temperature, the β phase can transform to the undesirable (brittle) intermediate ω phase (Donachie 2000; Froes 2015; Rajan et al. 2011). To prevent the formation of ω phase, a stabilization anneal is generally given for the α + β titanium alloys (Donachie 2000; Froes 2015). This annealing treatment produces a stable β phase capable of resisting further transformation when exposed to elevated temperatures in service. The α + β Ti64 alloy that is lean in β can be air cooled from the annealing temperature without impairing their stability (Donachie 2000; Campbell 2008).
Despite the advantages of β-annealed Ti64 alloys, notably in the thick sections required for large primary aircraft structure, little is known in detail about fatigue properties. In this study, the high cycle fatigue (HCF) and fatigue crack propagation (FCP) behaviors of β-annealed Ti64 alloy were investigated, and the results were compared to those of mill-annealed Ti64 alloy. The effects of tensile properties and crack nucleation mechanism on the HCF behavior of β-annealed Ti64 was discussed based on the detailed fractographic and micrographic observation. The mechanisms associated with the microstructure-sensitive FCP behavior of β-annealed Ti64 alloy was also discussed with a particular emphasis placed on the morphology of crack path.
To study the HCF and FCP behaviors of β-annealed Ti64 alloy, β-annealed Ti64 plate with a thickness of 70 mm were supplied without β stabilization after annealing. 3-mm thick, mill-annealed Ti64 alloy was also provided to compare the present test results of β-annealed Ti64 alloy to the specimen with general purpose heat treatment. Figure 1 schematically describes the heat treatment conditions used in this study. For the micrographic observation, the Ti64 specimens were polished and etched using a solution of Kroll’s reagent (85 mL H2O + 3 mL HNO3 + 5 mL HF) (Gammon et al. 1985), and an optical microscope was utilized. Figure 2 shows the optical micrographs of (a) β-annealed and (b) mill-annealed Ti64 specimen. The β-annealed Ti64 specimen showed lamellar microstructure of the colonies of acicular α platelets aligned with the same crystallographic orientation within prior β grain boundaries. Globular α phase and intergranular α layer along the β grain boundary were intermittently observed. The mill-annealed Ti64 alloy showed the equiaxed α grains with an average size of 10 μm, and the particle-like transformed β phase along α grain boundaries.
Flat tensile specimens and hour-glass typed, stress-controlled (S-N) fatigue specimens were prepared from Ti64 plate with the tensile axis parallel to the longitudinal (L) direction. The compact tension (CT) specimens were also prepared form the plate with L (longitudinal) -T (transverse) orientation. Figure 3 shows the schematic illustration of (a) tensile specimen, (b) S-N fatigue specimen, and (c) CT specimen used in this study. The tensile tests were performed on a screw-driven universal testing machine (model: MTDI UT-100) at a nominal strain rate of 1 × 10-3 /sec. The S-N fatigue tests were conducted on a servo-hydraulic testing machine (model: Instron 8516) with the applied stresses ranging between 170 and 405 MPa at an R ratio of 0.1 under a uniaxial loading condition with a sinusoidal frequency of 30 Hz at 25 °C in accordance with ASTM E466 (ASTM Standard E466 2002). The run-out of the S-N fatigue tests was defined as those not failed up to 5 × 106 cycles. The scanning electron microscope (SEM) analysis was conducted on the tensile and S-N fatigue tested specimens to examine the fracture mode. The fatigue crack propagation (FCP) tests were carried out on the CT specimens at 25 °C in accordance with ASTM E647 (ASTM Standard E647 2002) using a servo-hydraulic testing machine (model: Instron 8516). The FCP tests were performed with a sinusoidal frequency of 10 Hz and at the R ratios of 0.1 and 0.7. The fatigue crack length was automatically measured by using a DCPD (direct current potential drop) method. The fracture mode analysis and the crack path examination were conducted on the FCP tested specimens by using an SEM and an optical microscope.
Results and discussion
Figure 4 shows the typical stress-strain curves of β-annealed and mill-annealed Ti64 specimens with the loading axis parallel to the rolling direction. The test results are summarized in Table 1, where each value represents the average of duplicate test results. As expected, both strength and ductility were lower for the β-annealed Ti64 specimen than the mill-annealed counterpart (Campbell 2011; Jeong et al. 2016a). It has been established that effective slip length is an important microstructural parameter affecting the tensile properties of α/β Ti alloys. Primary α grain boundaries of mill-annealed Ti64 specimen, for example, act as barriers for dislocations to move, and smaller α grain size may reduce the effective slip length, enhancing both strength and ductility (Lütjering 1998; Ziaja et al. 2001). For the lamellar microstructure of acicular α phase, the aligned α platelets are separated by thin ribs of β phase forming an α/β boundary which does not act as an effective barrier to slip. However, the colony of α platelets has a certain crystallographic orientation, and the colony boundaries are effective barriers to slip along with prior β grain boundaries (Lütjering 1998; Ziaja et al. 2001; Lütjering and Williams 2013). The colony size, as well as prior β grain size, therefore play an important role in determining the tensile properties of β-annealed Ti64 alloy (Lütjering 1998; Ziaja et al. 2001). The average colony size in the β-annealed Ti64 specimen was 84 μm, while the average α grain size was 10 μm for the mill-annealed counterpart. Such a large difference in the effective slip length explained the inferior strength and ductility of β-annealed Ti64 specimen. Figure 5 shows the SEM fractographs of tensile-fractured (a) β-annealed and (b) mill-annealed Ti64 specimens. Large cleavage facets were observed for the β-annealed Ti64 specimen with dimples intermittently located in between these facets. These cleavage facets appeared to be the result of tensile fracture occurring by cutting through the aligned α platelets. The plastic instability in between the facets were believed to induce dimpled rupture. Unlike the β-annealed Ti64 specimens, the mill-annealed counterpart showed a cup-and-cone type of ductile fracture with fine dimples covering the fracture surface.
The crack nucleation under fatigue loading largely determines the resistance to HCF of Ti alloys (Nicholas 2006). Since yield strength is the indicative of the resistance to slip deformation inducing crack nucleation on smooth surface, it is therefore one of the most important parameters affecting the HCF resistance (Jung et al. 2014; Jeong et al. 2013). As in the case of tensile behavior, the microstructure can have a significant influence on the HCF resistance of Ti64 alloy. For the mill-annealed Ti64 specimen, smaller primary α grain tends to improve the HCF resistance since yield strength increases with decreasing primary α grain size. Higher applied stress is then required to initiate a crack in primary α grain by slip band cracking (Lucas and Konieczny 1971; Bowen and Stubbington 1973). The smaller primary α grain also induces higher density of α/α grain boundaries, which may increase the resistance to HCF by retarding the crack growth with the grain boundaries acting as microstructural barriers (Demulsant and Mendez 1995). For the β-annealed Ti64 specimen, the microstructural factors affecting the HCF behavior include the sizes of colony, α platelet and prior β grain. Smaller sizes of colony and prior β grain in the β-annealed Ti64 specimen increase the resistance to HCF by reducing effective slip length, as in the mill-annealed counterpart (Lütjering 1998; Ziaja et al. 2001; Lucas and Konieczny 1971; Bowen and Stubbington 1973; Demulsant and Mendez 1995). The narrower aligned α platelets within colonies can further suppress the crack initiation by slip band cracking, since the crack needs to cross through more of the β ribs in the aligned α platelets (Eylon and Pierce 1976; Bania et al. 1982; Ruppen et al. 1979). As in the mill-annealed Ti64 specimen, colony boundaries and prior β grain boundaries in the β-annealed specimen can act as microstructural barriers for crack to grow, improving the resistance to HCF.
Figure 6a shows the S-N fatigue curves of β-annealed and mill-annealed Ti64 specimens, uniaxially fatigued at an R ratio of 0.1. This figure clearly shows that the resistance to S-N fatigue of β-annealed Ti64 was inferior to that of mill-annealed counterpart. As mentioned previously, such a trend in Fig. 6a can be mostly due to lower yield strength of β-annealed Ti64 alloy as compared to the mill-annealed counterpart. To confirm such a notion, the S-N fatigue curves of β-annealed and mill-annealed Ti64 specimens were normalized by the yield strength values. As shown in Fig. 6b, two fatigue curves became closely merged, suggesting that the yield strength played an important role in determining the HCF behavior of Ti64 alloy. It was also notable in Fig. 6b that there existed considerable difference between two normalized fatigue curves. It was therefore suggested that, the microstructural characteristics, as well as yield strength, may influence the HCF resistance of Ti64 specimen by affecting fatigue crack nucleation. The fatigue cracks in α + β Ti alloys tend to initiate in slip bands at the surface of large α grain in an early stage of fatigue life (Kim et al. 2013; Sung et al. 2016). Under an applied stress level close to fatigue limit, it has been reported that crack starts to form at the interface between α and β phases later in the fatigue life (Hines and Lütjering 1999). Figure 7 shows the micrographic examination of crack nucleation on the etched specimen’s surface and the matching SEM fractographs for the mill-annealed Ti64 specimen fatigued at an R ratio of 0.1. Basically, two different types of crack initiation were observed, including (a) an intragranular cracking within α grain, and (b) a cracking at α/β boundary. The present observation in Fig. 7 matched to the previously reported nucleation sites of fatigue crack nucleation in mill-annealed Ti64 alloys (Jeong et al. 2016a). The matching SEM fractographs reflected the nature of crack nucleation site, showing particle-like β phase on the fracture surface for the cracking case at α/β boundary. In general, coarse lamellar microstructures with colonies of aligned α and extended planar slip across these colonies often have lower resistance to HCF as compared to the microstructure of fine-grained equiaxed α phase with the reduced effective slip lengths (Lütjering 1998; Ziaja et al. 2001). To better understand the HCF behavior of β-annealed Ti64 alloy, the preferential sites for crack nucleation and the fracture mode were examined in the fatigue-failed specimen. Figure 8 shows the specimen’s surface showing the crack initiation and the SEM fractographs of fatigue-tested β-annealed Ti64 specimen. Unlike mill-annealed counterparts, the fatigue cracks in the β-annealed Ti64 specimen were formed along the colony boundaries. Once a small crack was initiated at the α/β interface by slip band cracking, the crack tended to propagate in a brittle cleavage manner forming large facets on the fracture surface. Considering the pseudo-cleavage nature of crack growth for the mill-annealed Ti64 specimen (Fig. 7), substantial difference in crack growth between two annealing conditions was expected. The present fractographic and micrographic examinations in Figs. 7 and 8 suggested that the ease of crack nucleation, as well as the lower yield strength, contributed to the inferior resistance to HCF of β-annealed Ti64 specimen as compared to the mill-annealed counterpart. It was clearly noted that the lamellar structure in β-annealed Ti64 specimens led to easy crack initiation by slip band cracking along α/β interface as compared to quasi-cleavage cracking in α grain or α/particle-like β interface for the mill-annealed counterpart.
Figure 9 shows the da/dN-ΔK curves of β-annealed and mill-annealed Ti64 specimens, FCP-tested at an R ratio of (a) 0.1 and (b) 0.7. It was noted that the FCP rates of β-annealed Ti64 specimen were substantially lower than those of mill-annealed counterpart at low and intermediate ΔK regimes at both R ratios of 0.1 and 0.7. Above the ΔK value of 30 MPa√m at an R ratio of 0.1 and 10 MPa√m at an R ratio of 0.7, the FCP rates of β-annealed and mill-annealed specimens became similar with each other. As expected, the increase in R ratio from 0.1 to 0.7 increased the FCP rates of each specimen, particularly in low ΔK regime. The effect of R ratio on the FCP behavior is mainly attributed to crack closure effects, in which crack faces contact each other with the crack closure stress intensity factor, Kcl lower than the minimum applied stress intensity factor, Kmin (Starke and Williams 1989; Jeong et al. 2015a). It was noted in Fig. 9 that the difference in the FCP rates of Ti64 specimens between β-annealing and mill-annealing in low ΔK regime tended to decrease with increasing R ratio from 0.1 to 0.7. In order to understand the reason for the improved resistance to FCP with β-annealing at low and intermediate ΔK regimes, the crack path was examined by using an optical microscope. For this examination, selected specimens were polished, etched, FCP tested, and the crack paths were photo-documented. Figure 10 shows the crack paths of β-annealed Ti64 specimen, FCP tested at an R ratio of 0.1 and documented at (a) ΔKth regime, (b) the ΔK of 20 MPa√m, and (c) the ΔK of 40 MPa√m. For comparison, the crack path of mill-annealed Ti64 specimen examined at ΔKth regime is included in Fig. 10d. A number of bifurcated cracks were observed for the β-annealed Ti64 specimen at low and intermediate ΔK regime. The bifurcated cracks mostly cut through the packets of α colonies. When cracks were favorably oriented relative to the microstructural orientation (i.e., packet orientation, grain boundary orientation), some cracks grew following prior β grain boundaries or packet boundaries. The mill-annealed Ti64 specimen with equiaxed α grains, on the other hand, did not show any notable crack bifurcation, regardless of applied ΔK. It was notable that the crack bifurcation in the β-annealed Ti64 specimen was no longer observed at high ΔK regime, as shown in Fig. 10c. The fatigue crack growth of α + β Ti alloys into adjoining, but differently oriented, α colonies has been known to involve significant crack deflection, crack bifurcation, and secondary crack formation, because of the limited number of slip systems available within hcp α phase (Halliday and Beevers 1981; Hicks et al. 1983; Suresh 1983; Suresh 1985; Suresh and Ritchie 1982). The present observation confirmed that the lamellar structure encouraged the crack bifurcation at low and intermediate ΔK regime, which in turn reduced the effective ΔK value and eventually decreased the FCP rates. The crack closure would be higher for the microstructure with bifurcated crack, further reducing the FCP rates particularly at low ΔK regime. The superior crack growth resistance of β-annealed Ti64 specimens with the lamellar microstructure of α colony is therefore attributable to a crack path characterized by high degree of crack deflection, bifurcation and secondary cracking. Figure 11 shows the crack paths of β-annealed Ti64 specimen, FCP tested at an R ratio of 0.7 and documented at (a) ΔKth regime and (b) the ΔK of 40 MPa√m. It was notable at high R ratio of 0.7 that the crack bifurcation and deflection were no longer observed even at low ΔK regime. No crack meandering by bifurcation and deflection appeared to be responsible for the less notable improvement in the resistance to FCP at an R ratio of 0.7 with the β-annealing as compared to that at R ratio of 0.1. The present observation also suggested there exists a critical Kmax value over which the crack bifurcation no longer occur in the β-annealed Ti64 specimen.
Figures 12 and 13 show the SEM fractographs of FCP-tested β-annealed Ti64 specimen, documented (a) in the near-threshold ΔK regime and (b) at the ΔK of 30 MPa√m, respectively, at an R ratio of 0.1 (Fig. 12) and 0.7 (Fig. 13). Previous studies by the authors on the FCP behavior of mill-annealed Ti64 specimen showed fine transgranular facets by quasi-cleavage in the near-threshold ΔK regime (Jeong et al. 2016b). With increasing ΔK, quasi-cleavage transgranular facets became finer. For the β-annealed Ti64 specimen, large transgranular cleavage facets were observed in near-threshold ΔK regime. Considering the size of each facet it was suggested that both colony boundaries and β grain boundaries affected the FCP behavior of β-annealed Ti64 specimen (Kim et al. 2011; Jeong et al. 2015b; Jeong et al. 2014). With increasing ΔK, quasi-cleavage faceting became dominant for the β-annealed specimen. Due to the crack branching, secondary cracks were intermittently observed on the fracture surface. Basically, the trend observed at an R ratio of 0.1 in Fig. 12 for the β-annealed Ti64 specimen also prevailed at high R ratio of 0.7, showing large transgranular facets on the fracture surface.
The high cycle fatigue (HCF) and fatigue crack propagation (FCP) behaviors of β-annealed Ti64 alloy were studied, and the following conclusions are drawn.
The β-annealed Ti64 specimen showed inferior tensile properties as compared to the mill-annealed counterpart. The decrease in tensile strength and ductility with β-annealing was related to the increase in the effective slip length as colony boundaries, as well as prior β grain boundaries, acted as microstructural barriers for dislocation movement.
Along with the reduced yield strength with β-annealing, the resistance to HCF of β-annealed Ti64 specimen was also lower than that of mill-annealed counterpart. Relatively easy fatigue crack initiation at the colony boundaries of β-annealed Ti64 specimen, as compared to the initiation either at α/β interface or within α grain for the mill-annealed counterpart, further reduce the resistance to HCF.
Due to the extrinsic effect of crack branching and deflection, the resistance to FCP of β-annealed Ti64 specimen was higher than that of mill-annealed counterpart in low and intermediate ΔK regime at both R ratios of 0.1 and 0.7. At high ΔK regime, the crack branching and deflection was no longer observed, and the FCP rates of β-annealed Ti64 specimen became similar to those of mill-annealed counterpart.
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This work has been supported by the Engineering Research Center (ERC) Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Education, Science and Technology (2011-0030801). This work was also supported by the Industrial Technology Innovation Program (10050561, Forming, Post-treatment and Assembly Manufacturing Technology for Nozzle Fairing of 17700 lbs Supersonic Engine) funded By the Ministry of Trade, Industry and Energy (MI, Korea), and the Fundamental Research Program of the Korea Institute of Materials Science (KIMS).
DH conducted the experiments, collected the data, and wrote the paper. YN, M and SS guided and supported this work and contributed with their expertise and advices to write a paper. All authors read and approved the final manuscript.
TThe authors declare that they have no competing interests.