Application of a Cohesive Zone Model for Simulating Fatigue Crack Growth from Moderate to High Δ K Levels of Inconel 718

A cyclic cohesive zone model is applied to characterize the fatigue crack growth behavior of a IN718 superalloy which is frequently used in aerospace components. In order to improve the limitation of fracture mechanics-based models, besides the predictions of the moderate fatigue crack growth rates at the Paris’ regime and the high fatigue crack growth rates at the high stress intensity factor ΔK levels, the present work is also aimed at simulating the material damage uniformly and examining the influence of the cohesive model parameters on fatigue crack growth systematically. The gradual loss of the stress-bearing ability of the material is considered through the degradation of a novel cohesive envelope. The experimental data of cracked specimens are used to validate the simulation result. Based on the reasonable estimation for the model parameters, the fatigue crack growth from moderate to high ΔK levels can be reproduced under the small-scale yielding condition, which is in fair agreement with the experimental results.


Introduction
Most of the service failures of aerospace components such as landing gears, turbine blades, fastener joints, and so on are caused by fatigue associated with cyclic loading.The fatigue damage of structural metals normally is associated with the initiation of macrocracks (the nucleation and growth of microcracks), such that a few dominated macrocracks grow until the final unstable fracture happens.By taking into account material degradation instead of one single major crack, continuum damage mechanics provides a sophisticated framework for the fatigue crack initiation analysis of metallic materials [1], while the fracture mechanics-based models are dominated approaches in simulating fatigue crack growth [2].
One of the extensively used models for predicting fatigue crack growth is the Paris' law [3] which relates the range of the stress intensity factor ΔK and the crack growth rate da/dN through a power law in double logarithmic coordinates.Generally, the relationship between da/dN and ΔK for most of metallic materials can be divided into three stages [4], as illustrated in Figure 1.Regime I corresponds to the formation of a fatigue crack at the low ΔK, where crack growth cannot be observed if ΔK is less than the threshold ΔK th .Regime II usually maintains the Paris' law, which exhibits the moderate fatigue crack growth rate (i.e., 10 −6 mm/cycle <da/dN < 10 −3 mm/cycle).The high crack growth rate (i.e., da/dN > 10 −3 mm/cycle) achieves at Regime III in which ΔK asymptotically approaches the fracture toughness ΔK c .Fatigue life predictions in engineering design have much success with the modifications of the Paris' law to determine crack growth rates [5,6].
Since elastic or the small-scale yielding (SSY) condition at crack-tip is assumed in the K-based models, many attractive models have also been proposed to simulate fatigue crack growth with considerable plastic deformations [6][7][8][9][10].One representative model proposed by Dowling and Begley [7] is constructed by replacing ΔK with ΔJ-integral to extend the Paris' law into the large-scale yielding (LSY) conditions.However, some researchers [11,12] have pointed out that J-integral is invalid upon unloading.Although other researchers [10] found that ΔJ-integral still maintains its path independence under cyclic loadings, nevertheless, it is a considerable issue how to use ΔJ-integral correctly in fatigue crack growth simulations.
The cohesive zone model (CZM) is another reliable approach which can describe the gradual degradation of stress-carrying ability at a propagating crack-tip within the framework of the nonlinear fracture mechanics.CZMs were firstly proposed by Dugdale [13] and Barenblatt [14] to consider the presence of process zone at crack-tip, where the local degradation during crack growth is determined by a given constitutive law (cohesive law) to relate the traction with the magnitude of material separation.Except the applications in brittle [15] and composite materials [16], cohesive models have been widely used in simulating the ductile fracture of metallic materials.Tvergaard and Hutchinson [17] introduced a trapeziform cohesive law to investigate crack growth resistance during the fracture process of an elasticplastic solid.Chen et al. [18] simulated the ductile crack growth of the thick CT specimens made of the pressure vessel steel using a polynomial cohesive law.Uthaisangsuk et al. [19] applied a CZM between martensitic islands and ferritic grains to consider interface debonding in the dual-phase microstructure of DP600 steel.Li et al. [20] studied the ductile fracture of a notched Ti-6Al-4V specimen using a CZM.Several authors [21] summarized classifications and applications of the CZM, which demonstrate the importance of cohesive models in simulating ductile fracture.
For fatigue crack calculations, the material degradation under cyclic loading must be considered; namely, the cyclic cohesive zone model (CCZM) should be applied to simulate fatigue crack growth.So far, there are many existing CCZMs that are able to describe the linear Paris' region (Regime II) behavior.The first CCZM disinterring the Paris-like behavior of fatigue crack growth for metallic materials was proposed by Nguyen et al. [22].They simulated fatigue crack growth of a central cracked aluminum specimen and demonstrated that the CCZM is capable of reproducing the Paris' law.The unloading-reloading hysteresis was applied to account for dissipative mechanisms, which prevents the "shakedown" effect efficiently in the crack growth process.However, they did not mention the predictive ability of the model in Regime III.Maiti and Geubelle [23] introduced a bilinear cohesive law with an irreversible unloading-loading path to assess capacity of the model for predicting fatigue crack growth in polymers.Although they concluded that the developed model can be used in both Regime II and Regime III for an epoxy, they did not show the applications of the proposed model in simulating ductile materials.Roe and Siegmund [12] considered the effects of the interface fatigue crack growth under different loading modes using an irreversible CZM, and while most of the simulation results were performed under the linear Paris' region, high rates associated with Regime III were not demonstrated.Ural et al. [24] used a damage-based cohesive model to predict the fatigue crack growth behavior in Regime II of an aluminum alloy.However, the application of this model has not been identified in Regime III also.Li and Yuan [25] used a normal stressdominated cohesive model to simulate fatigue crack growth of cracked and notched specimen and reproduced the linear Paris-like behavior at different loading ratios; nonetheless, the predictive ability in Regime III has not been considered in the CZM.Jimenez and Duddu [26] proposed a strain energy release rate-dependent CZM to model high cycle fatigue delamination of the composite materials under both mode I and mixed mode loadings, and they pointed out that the CZM is suitable for the constant amplitude loading in Regime II and also expected to extended the model to describe all three regimes in fatigue crack simulations.CCZMs can also be applied in analyzing the elastoplastic fatigue cracks by introducing some stress triaxialitydependent parameters [27,28]; that is, Jha and Banerjee [28] proposed a triaxiality-dependent cohesive model to  2 International Journal of Aerospace Engineering simulate the fatigue failure of ductile metals and proved that the CZM is suitable for the geometries with different stress states.Similarly, these models [27,28] do not mention their applications for fatigue crack growth at the high ΔK levels in Regime III.Although the Paris-like behavior which corresponds to the moderate ΔK levels in Regime II can be predicted by using the aforementioned CCZMs [11,[22][23][24][25][26][27], this is not the advantage of CCZMs, since the Paris regime associated with SSY has already been described successfully according to the K-based models.In order to resolve the more challenging task that to simulate the high fatigue crack growth rates in Regime III of the metallic materials, a CCZM was proposed in our previous work [29] in which two damage variables were defined to represent monotonic damage and fatigue damage, respectively.In fact, it is not easy to distinguish these two different damage mechanisms in fatigue crack growth before the final rupture occurs; thus, it is better to describe the material damage evolution uniformly.Meanwhile, it is anticipated that CCZMs have the potential to predict high fatigue crack growth rates in Regime III under the LSY conditions.For the purpose of easing the difficulty level for cohesive modeling of fatigue crack growth at LSY, the predictive ability of CCZMs in simulating high fatigue crack growth rates at SSY should be verified systematically.
Therefore, the objective of this work is to examine a CCZM for predicting high fatigue crack growth rates corresponding to Regime III under the SSY conditions.Meanwhile, the present study attempts to describe the material damage evolution uniformly and identify the effects of the cohesive model parameters on fatigue crack growth under both moderate and high ΔK levels.The contents of this paper include the following aspects: in Section 2, the detailed formulations of the CCZM are introduced.In Section 3, the identification of the model parameters is performed firstly, then the numerical results are presented according to the compact-tension (CT) specimens and the single-edge notched (SEN) specimens made of the IN718 superalloy and validated against the experimental data from literatures.Finally, the major conclusions are summarized in Section 4.

Cohesive Zone Model
The cohesive model has the ability to consider the ductile rupture of the metallic materials under various loading conditions.For fatigue crack growth simulations, the CCZM has to be able to describe accumulative damage associated with cyclic loading.Assume that the degradation of the original cohesive envelope occurs with damage accumulation, and the constitutive law under fatigue loading is defined as where the normal traction T n is assumed to be a piecewise function depending upon the normal separation δ n .δ 0 is the characteristic length of the cohesive law, which is denoted as the cohesive length.δ u denotes the maximum normal separation above which the normal traction vanishes.Following the concept from the continuum damage models, the damage variable D = t Ddt stands for the material degradation and represents failure if D approaches 1. σ max = σ max,0 1 − D is the cohesive strength used to identify the peak value of the normal traction and σ max,0 is the initial cohesive strength.
The original cohesive law under monotonic loading can be obtained by substituting D = 0 into (1).The parameter δ c corresponds to the material separation relating to the damage variable D and δ 0 ≤ δ c ≤ δ u .For both constant and variable amplitude loadings, the damage evolution equation suggested by Roe and Siegmund [12] can be applied to reflect the accumulative damage for the metallic materials, which reads where d Σ is the accumulated cohesive length used to scale the increment of the normal separation δ n and δ = t |δ n |dt.σ f is the cohesive endurance limit.The Macaulay brackets are used to signify nonnegative value of damage evolution, and the Heaviside function H states that damage initiates at δ > δ 0 .
The novel cohesive envelope determined by (1) will degrade and change its shape correspondingly associated with the damage accumulation, and this characteristic is the major difference between the current model and other CCZMs [11,12,20,[22][23][24][25][26][27][28].For example, in [25], the combination use of (2) and the cohesive envelope of the exponential form are performed to simulate fatigue crack growth; however, this combination results in the contradictory damage evolution at δ n > δ 0 if a slightly larger value of σ f /σ max,0 is provided, and this problem can be solved by using (1).As mentioned above, the similar CCZM has been proposed to investigate the mixed mode fatigue crack growth in our previous simulations [29], the difference between these two models is that the current one does not introduce the monotonic damage, the material degradation under cyclic loadings is described uniformly by (2), and the monotonic damage is determined by the cohesive envelope implicitly.Actually, the combination of (1) and (2) has the capacity to simulate fatigue crack growth at the high ΔK levels, the applications need not be distinguished between monotonic damage and fatigue damage as introduced in [29], the key point in such simulations is the form of (1), and more details will be performed in Section 3.
For the numerical implementation of the model under each unloading-reloading cycle, assume that the residual separation exists after a complete unloading cycle as plastic 3 International Journal of Aerospace Engineering deformations, and the corresponding unloading-reloading path can be denoted by where T n is the traction at time t + Δt related to the separation δ n according to the cohesive stiffness k n .T n,t and δ n,t are the traction and the separation at time t, respectively.As shown in Figure 2(a), assume that the rising segment (1 → 2) of the loading sequence results in the separation of a material point at the cohesive zone.In order to explain the operating mechanism of the model under cyclic loading in detail, two different cases are considered, namely, δ n ≤ δ 0 (Figure 2(b)) and δ n > δ 0 (Figure 2(c)).Upon unloading, the path (2 → 3) follows (3) without damage evolution.The contact of two cohesive surfaces is constrained by introducing a penalized equation as where A is the penalty stiffness.Here, we should mention that this contact algorithm is applied to simulate crack closure explicitly.The crack closure effects are related to the plastic deformation of the bulk material around the crack-tip implicitly under cyclic loading.The reloading path (3 → a) specified by (3) deviates from the previous unloading path due to damage evolution.At the subsequent loading segment (3 → 4), the value of T n corresponding to reloading may reach the degraded cohesive envelope T 1 n at a. Upon further reloading, the value of T n moves along the degraded envelope T 1 n at time t; however, the continued damage accumulation through (2) makes it move along the subsequent degraded cohesive envelope T 2 n at time t + Δt.The dot lines in Figures 2(b) and 2(c) are two degraded cohesive envelopes corresponding to δ 1 c and δ 2 c , respectively.In both cases, if the loading level makes the reloading path move along the descending part of the degraded cohesive envelop, there is no damage accumulation that will occur and the material degradation is described by (1) implicitly.
The above CCZM has been implemented based on the user interface UMAT of the commercial code ABAQUS via the cohesive element [30].Since the numerical simulations are performed according to the ABAQUS/Standard solver, both the updated cohesive traction and the material Jacobian matrix should be provided for constructing the internal nodal force vector and the cohesive stiffness matrix in UMAT.The standard Newton method is applied to solve the global nonlinear equations, and the default values for the solution control parameters are adopted.The global convergence rule is checked at the end of each time  4 International Journal of Aerospace Engineering increment, such that the tolerance limit on the residual force can be fulfilled.

Model Validation
In the present study, the influence of model parameters on fatigue crack growth will be verified systematically; meanwhile, the predictive ability of the model for the high fatigue crack rates in Regime III will be validated experimentally.
The material under investigation is a nickel-based superalloy IN718 which is widely used in aeroengine components due to its high yield stress, excellent fatigue resistance, and so on in severe conditions [31].In modeling a CT specimen with the initial crack, the length is a = 25 mm and the thickness is B = 12 5 mm.The material properties are as follows: Young's modulus E = 200 GPa, Poisson's ratio v = 0 3, the initial yield stress σ y = 1196 MPa, and the plane strain fracture toughness K Ic = 125 MPa m 1/2 .The J 2 plasticity is applied to describe the plastic behavior of the alloy, and the relationship between true stress σ and true plastic strain ε p is described by the Holomon's equation as where the bulk modulus K = 1531 MPa and the strain hardening exponent n = 0 015.We note from the perspective of cohesive modeling for fatigue crack that the isotropic hardening is often assumed to simulate the material response approximately without knowing the exact cyclic deformation behavior of the bulk material [11,28,32].However, the more accurate cyclic plasticity model should be determined experimentally as mentioned in [33].Due to the symmetry, only the upper half of the specimen is modeled under the plane strain condition, as shown in Figure 3.The whole finiteelement model consists of 1725 elements and 1872 nodes.The cohesive zone is predefined along the crack growth path using 240 COH2D4 elements which are uniformly distributed along the ligament of the specimen with the element length of 0.1 mm.The CPE4 elements are used for the rest of the regions.
3.1.Identification of Model Parameters.Based on previous descriptions, the model parameters can be divided into two types.The monotonic model parameters include cohesive strength σ max,0 , cohesive length δ 0 , and cohesive energy Γ 0 .The cyclic model parameters are the accumulative length d Σ and the cohesive endurance limit σ f .Omitting shear stress in the cohesive zone, only the normal traction is active under the mode I crack growth condition.The cohesive energy Γ 0 is determined by integration of the monotonic cohesive envelope as follows: where the form of T n is represented by (1) with D = 0.The monotonic cohesive envelope can be constructed through the initial cohesive strength σ max,0 , the cohesive length δ 0 , and the cohesive energy Γ 0 .Under the SSY conditions, the cohesive energy is related to the plain strain fracture toughness K Ic based on the Irwin's relation as follows:

International Journal of Aerospace Engineering
According to (8), the cohesive energy is Γ 0 = 7 1 × 10 4 J/ m 2 in the present analysis.The cohesive strength σ max,0 = 3900 MPa is used, which is nearly three times above the initial yield stress of IN718 according to the suggestion in [34], where the corresponding cohesive length σ 0 = 0 003 m m.Actually, the relationship between the initial cohesive strength and cohesive length can be attributed to the effect of the initial cohesive stiffness k n .The choice related to k n should guarantee that the cohesive zone does not influence the overall compliance before damage initiation and normally a higher value of k n is used.Since the cohesive energy is the work needed to create a unit area of two mating fracture surfaces, the resulting δ u = 0 017 mm is obtained according to (1) with D = 0.
Identification of the influence of the model parameters is performed using the CT specimen under constant loading amplitudes at the loading ratio R = 0 1, where R = F min / F max with F max and F min are the maximum and minimum of the uniaxial applied force F, respectively.The nominal stress intensity factor is applied to describe the stress field at crack-tip.The range of the stress intensity factor ΔK for the CT specimens can be calculated through [35]: 0 886 + 4 64ζ − 13 32ζ 2 + 14 72ζ 3 − 5 6ζ 4 , 9 where ζ = a/W.This formulation is accurate within 0.5% error over the range 0.2 ≤ζ ≤ 1.
The effect of the accumulative length d Σ to the crack growth length curve is indicated in Figure 4(a), where the initial stress intensity factor ΔK i = 76 MPa m 1/2 .At a given crack growth length Δa, the lower value of d Σ corresponds to the higher crack growth rate for the same value of σ f / σ max,0 .In comparison with the number of loading cycles to the final failure between d Σ = 20 δ 0 and d Σ = 25 δ 0 , the critical crack growth length of approx.5.5 mm is achieved under both d Σ = 20 δ 0 and d Σ = 25 δ 0 at failure.Theoretically, the critical crack length should be reached at d Σ = 10 δ 0 also; however, the FE calculation is aborted since the high damage evolution rate associated with d Σ = 10 δ 0 is so fast that the mesh resolution of 0.1 mm at crack-tip cannot capture the crack growth rate before the final failure.The effect of σ f /σ max,0 on the crack growth curves is shown in Figure 4(b) by comparing two different values of σ f /σ max,0 at d Σ = 10 δ 0 , where the higher crack growth rate is accompanied by the lower value of σ f / σ max,0 at a given crack length.Based on Figure 4, we can conclude that the critical crack length is only determined by the monotonic model parameters together with the ΔK level.
The effect of d Σ on the da/dN versus ΔK curve is shown in Figure 5(a), where the da/dN data are determined based on the corresponding a − N curves (see Figure 4).In order to examine the effects of cyclic model parameters on fatigue crack growth in the Paris' region, the numerical results of the lower loading level F max = 20 kN associated with ΔK i = 63 MPa m 1/2 is also displayed.The accumulative length d Σ acts like the intercept coefficient C which operates in the Paris' law, that is, da/dN = C ΔK m .It plays a role  7 International Journal of Aerospace Engineering in increasing or decreasing crack growth rate in all portions at a certain value of σ f /σ max,0 .In contrast, σ f /σ max,0 has a tendency to modify the slope of the da/dN versus ΔK curve as the parameter m of the Paris' law, as shown in Figure 5(b).However, the effects of the cyclic model parameters are also influenced by the monotonic model parameters; namely, the crack growth rate is accelerated inevitably as the ΔK level approaches the critical value ΔK c = 1 − R K Ic in Regime III before the final failure.The above results reveal that the high fatigue crack growth rates at high ΔK levels can be captured reasonably based on the current model and the uniform damage evolution equation can be applied in such simulations.

Comparison with Experiments.
After the parameter identification, the next the predictive ability of the model will be examined using the CT specimen as displayed in Figure 3(a).The experimental data in validations are obtained by digitizing the results reported by Yamada and Newman [36] and Newman et al. [37], as shown in Figure 6, where the fatigue crack growth tests were performed by using the CT specimens and the SEN specimens at R = 0 1, respectively.The experimental results are fitted according to the Erdogan-Ratwani model [5].For the CT specimens, the experimental points can be well approximated by the following equation: where da/dN is in mm/cycle and ΔK is in MPa m 1/2 .For the SEN specimens, all points including the threshold region can be well described by the following equation: Three constant loading amplitudes, that is, F max = 17 kN, 18.5 kN, and 20 kN at R = 0 1, are applied to obtain the cyclic cohesive model parameters, where the corresponding initial stress intensity range are ΔK i = 54 MPa m 1/2 , ΔK i = 58 MPa m 1/2 , and ΔK i = 63 MPa m 1/2 , respectively.The fatigue crack growth simulations are performed to fit the experimental data associated with the moderate growth rates.As depicted in Figure 7, the fitting curve constructed by the aforementioned three ΔK levels correlates the experiments very well in the linear Paris' region.The corresponding crack growth versus the applied loading cycle curves are displayed in Figure 8, where the fastest crack growth rate is achieved under the highest ΔK level at a given crack length.The determined cyclic model parameters of IN718 are listed in Table 1.
For the fatigue crack growth simulation in Regime III, the constant loading amplitude is applied with F max = 24 kN at R = 0 1, which corresponds to the initial stress intensity factor range ΔK i = 76 MPa m 1/2 .In order to capture the local response of each material point along the crack growth path, four material points 1, 2, 3, and 4 located at the crack growth path are used to trace the material responses associated with    9 for both points 1 and 4, where the material damage is obtained based on (2) for the two material points.The traction of point 1 approaches 87% of the initial cohesive strength σ max,0 at the first loading cycle while the traction of point 4 is still small; namely, the traction of point 4 is only 10% of σ max,0 at the first loading cycle, as shown in Figure 10.Except for point 1 loses its stress-carrying ability at  Figure 10: The traction against the number of applied cycles is compared between (a) point 1 and (b) point 4, and the constant loading amplitude is carried out with F max = 24 kN at R = 0 1, which corresponds to the initial stress intensity factor range ΔK i = 76 MPa m 1/2 for the CT specimen.International Journal of Aerospace Engineering the 207th cycle, other points have no damage accumulations at the first 548 loading cycles such that their original cohesive stiffnesses still exist, since there are no damage evolutions for these points (see Figure 11).The damage initiation for point 4 starts after 1500 loading cycles, where the maximal value of the traction increases (up to 80% of σ max,0 ) at first and then decreases with the applied loading cycles until the material point is completely damaged (see Figure 10(b)), and this phenomenon is also true for points 2 and 3.
During the crack growth process, the distributions of the damage zone, the von-Mises stress, and the equivalent plastic strain under both the moderate and the high levels of ΔK are compared in Figure 12.The fatigue crack propagates from length a = 25 5 mm to 29.5 mm by measuring the length of the complete damage zone of the two levels of ΔK.For two cases, the von-Mises stress ahead of the current crack-tip is greater than the initial yield stress 1196 MPa and the obvious plastic zone is created gradually in the crack wake during crack growth.These results show that the material responses of both the cohesive zone and the surrounding bulk material are simulated reasonably.Figure 13 summarizes the numerical and experimental crack growth results under constant amplitude loading.The simulation associated with F max = 24 kN is the predicting result based on the determined model parameters listed in Table 1.The whole da/dN versus ΔK curves are assembled through these four different ΔK i levels.With increment of the crack length, da/dN becomes very high and approaches instability limited by the ΔK c at failure (see Figure 13).As indicated in Figure 1, fatigue crack growth in Regime II is largely influenced by the loading ratio and the frequency in the air; therefore, fatigue crack growth with moderate rates is irrelevant to the geometries of specimens.At high propagation rates as ΔK approaches to ΔK c , there is a good agreement between the prediction and the experiment of the SEN specimens, while a deviation between the simulation and the experiment of the CT specimens exists.Actually, the difference in experiment data also occurs between the CT and SEN specimens in Regime III due to the occurrence of ductile fracture.The ductile fracture process of metallic materials involves nucleation, growth, and coalescence of microvoids, which is greatly influenced by the stress state and may not be described, for example, by (1) simply, and the local constraint effect accompanied by the specimen geometry also affects the crack growth resistance.Nevertheless, based on the cyclic model parameters determined by the experimental data in Regime II, the numerical result captures the accelerated fatigue crack growth phenomenon of the experimental data in Regime III associated with the high ΔK levels.

Conclusions
In order to overcome the limitations of fracture mechanicsbased models, for example, the Paris' law or the ΔJ-integral-based model, for predicting elastic-plastic fatigue crack growth rates, the cyclic cohesive model is verified systematically on the fatigue crack growth of the IN718 alloy from moderate to high ΔK levels.Since ductile fracture occurs as the ΔK level approaches the fracture toughness, the model parameters determined from the experimental The simulations reveal that the novel cohesive envelope combined with one damage evolution equation can also be used to capture the accelerated fatigue crack growth behavior at the high ΔK levels, and there is no need to distinguish  11 International Journal of Aerospace Engineering between the monotonic damage and the fatigue damage as introduced in [29].The crack growth behaviors are largely affected by the accumulative length d Σ and the cohesive endurance limit σ f ; meanwhile, the effects of the cyclic model parameters are also influenced by the monotonic model parameters, that is, cohesive energy and the initial cohesive strength as the ΔK level approaches the critical value corresponding to the fracture toughness.
After the model parameter identification and the experimental validation, we confirm that the current model has the capacity to simulate the elastic-plastic fatigue crack growth behavior of IN718 at SSY, especially in Regime III.Furthermore, it remains for the next work to extend the application of the CCZM for simulating fatigue crack growth of other alloys at LSY.

Figure 3 :
Figure 3: (a) Sketch of a CT specimen (initial crack length a = 25 mm, width W = 50 mm, and thickness B = 12 5 mm) and (b) the FE mesh (a half of the specimen is modeled), and (c) points 1, 2, 3, and 4 correspond to the four integration points located along the crack growth path (the distance between two adjacent points is 1.2 mm), and the arrow indicates the initial crack-tip of the CT specimen.

Figure 4 :Figure 5 :
Figure 4: The effects of (a) the accumulative length d Σ and (b) σ f /σ max,0 on the crack growth curve.The constant loading amplitude is carried out with F max = 24 kN at R = 0 1, where the corresponding initial stress intensity factor range ΔK i = 76 MPa m 1/2 for the CT specimen.

Figure 6 :
Figure 6: Plot of the experimental result and the corresponding fitting curve by using the Erdogan-Ratwani model of the IN718 alloy for (a) the CT specimens and (b) the SEN specimens.

Figure 7 :
Figure 7: Plot of the experimental results and the corresponding fitting curves of the CCZM in the Paris' region.

Figure 8 :
Figure 8: The crack growth curves with varying ΔK i under the constant amplitude loading at R = 0 1.

Figure 9 :
Figure 9: The traction versus separation curves are compared between (a) point 1 and (b) point 4, and the constant loading amplitude is carried out with F max = 24 kN at R = 0 1, which corresponds to the initial stress intensity factor range ΔK i = 76 MPa m 1/2 for the CT specimen.

Figure 11 :
Figure 11: (a) The damage evolution and (b) the cohesive stiffness with the number of applied cycles are compared from point 1 to point 4, and the constant loading amplitude is carried out with F max = 24 kN at R = 0 1, which corresponds to the initial stress intensity factor range ΔK i = 76 MPa m 1/2 for the CT specimen.
[4]ure1: The typical fatigue crack growth rate with regard to the stress intensity factor curve for metallic materials, which is distinguished by three regimes.The corresponding influence factors and the crack propagation velocity at 50 Hz under different levels of the fatigue crack growth rate are also illustrated[4].

Table 1 :
Model parameters of IN718 used in simulations.