Crack growth equation

A crack growth equation is used for calculating the size of a fatigue crack growing from cyclic loads. The growth of a fatigue crack can result in catastrophic failure, particularly in the case of aircraft. When many growing fatigue cracks interact with one another it is known as widespread fatigue damage. A crack growth equation can be used to ensure safety, both in the design phase and during operation, by predicting the size of cracks. In critical structure, loads can be recorded and used to predict the size of cracks to ensure maintenance or retirement occurs prior to any of the cracks failing. Safety factors are used to reduce the predicted fatigue life to a service fatigue life because of the sensitivity of the fatigue life to the size and shape of crack initiating defects and the variability between assumed loading and actual loading experienced by a component.

Figure 1: Typical plot of crack growth rate versus the stress intensity range. The Paris–Erdogan equation fits the central linear region of Regime B.

Fatigue life can be divided into an initiation period and a crack growth period. Crack growth equations are used to predict the crack size starting from a given initial flaw and are typically based on experimental data obtained from constant amplitude fatigue tests.

One of the earliest crack growth equations based on the stress intensity factor range of a load cycle ($\Delta K$) is the Paris–Erdogan equation

${da \over dN}=C(\Delta K)^{m}$

where $a$ is the crack length and ${\rm {d}}a/{\rm {d}}N$ is the fatigue crack growth for a single load cycle $N$. A variety of crack growth equations similar to the Paris–Erdogan equation have been developed to include factors that affect the crack growth rate such as stress ratio, overloads and load history effects.

The stress intensity range can be calculated from the maximum and minimum stress intensity for a cycle

$\Delta K=K_{\text{max}}-K_{\text{min}}$

A geometry factor $\beta$ is used to relate the far field stress $\sigma$ to the crack tip stress intensity using

$K=\beta \sigma {\sqrt {\pi a}}$.

There are standard references containing the geometry factors for many different configurations.

History of crack propagation equations

Many crack propagation equations have been proposed over the years to improve prediction accuracy and incorporate a variety of effects. The works of Head, Frost and Dugdale, McEvily and Illg, and Liu on fatigue crack-growth behaviour laid the foundation in this topic. The general form of these crack propagation equations may be expressed as

${da \over dN}=f(\Delta \sigma ,a,C_{i}),$

where, the crack length is denoted by $a$, the number of cycles of load applied is given by $N$, the stress range by $\Delta \sigma$, and the material parameters by $C_{i}$. For symmetrical configurations, the length of the crack from the line of symmetry is defined as $a$ and is half of the total crack length $2a$.

Crack growth equations of the form $da/dN$ are not a true differential equation as they do not model the process of crack growth in a continuous manner throughout the loading cycle. As such, separate cycle counting or identification algorithms such as the commonly used rainflow-counting algorithm, are required to identify the maximum and minimum values in a cycle. Although developed for the stress/strain-life methods rainflow counting has also been shown to work for crack growth. There have been a small number of true derivative fatigue crack growth equations that have also been developed.

Factors affecting crack growth rate

Regimes

Figure 1 shows a typical plot of the rate of crack growth as a function of the alternating stress intensity or crack tip driving force $\Delta K$ plotted on log scales. The crack growth rate behaviour with respect to the alternating stress intensity can be explained in different regimes (see, figure 1) as follows

Regime A: At low growth rates, variations in microstructure, mean stress (or load ratio), and environment have significant effects on the crack propagation rates. It is observed at low load ratios that the growth rate is most sensitive to microstructure and in low strength materials it is most sensitive to load ratio.

Regime B: At mid-range of growth rates, variations in microstructure, mean stress (or load ratio), thickness, and environment have no significant effects on the crack propagation rates.

Regime C: At high growth rates, crack propagation is highly sensitive to the variations in microstructure, mean stress (or load ratio), and thickness. Environmental effects have relatively very less influence.

Stress ratio effect

Cycles with higher stress ratio $R=K_{\text{min}}}/{K_{\text{max}}\equiv P_{\text{min}}/{P_{\text{max}}}$ have an increased rate of crack growth. This effect is often explained using the crack closure concept which describes the observation that the crack faces can remain in contact with each other at loads above zero. This reduces the effective stress intensity factor range and the fatigue crack growth rate.

Sequence effects

A $da/dN$ equation gives the rate of growth for a single cycle, but when the loading is not constant amplitude, changes in the loading can lead to temporary increases or decreases in the rate of growth. Additional equations have been developed to deal with some of these cases. The rate of growth is retarded when an overload occurs in a loading sequence. These loads generate are plastic zone that may delay the rate of growth. Two notable equations for modelling the delays occurring while the crack grows through the overload region are:

The Wheeler model (1972)

$\left({\frac {da}{dN}}\right)_{\text{VA}}=\beta \left({\frac {da}{dN}}\right)_{\text{CA}}$ with $\beta =\left({\frac {r_{\text{pi}}}{r_{\text{max}}}}\right)^{k}$

where $r_{\text{pi}}$ is the plastic zone corresponding to the ith cycle that occurs post the overload and $r_{\text{max}}$ is the distance between the crack and the extent of the plastic zone at the overload.

The Willenborg model

Crack growth equations

Threshold equation

To predict the crack growth rate at the near threshold region, the following relation has been used

${da \over dN}=A\left(\Delta K-\Delta K_{\text{th}}\right)^{p}.$

Paris–Erdoğan equation

To predict the crack growth rate in the intermediate regime, the Paris–Erdoğan equation is used

${da \over dN}=C\left(\Delta K\right)^{m}.$

Forman equation

In 1967, Forman proposed the following relation to account for the increased growth rates due to stress ratio and when approaching the fracture toughness $K_{\text{c}}$

${da \over dN}={\frac {C(\Delta K)^{n}}{(1-R)K_{\text{c}}-\Delta K}}$

McEvily–Groeger equation

McEvily and Groeger proposed the following power-law relationship which considers the effects of both high and low values of $\Delta K$

${da \over dN}=A(\Delta K-\Delta K_{\text{th}})^{2}{\Big [}1+{\frac {\Delta K}{K_{\text{Ic}}-K_{\text{max}}}}{\Big ]}$.

NASGRO equation

The NASGRO equation is used in the crack growth programs AFGROW, FASTRAN and NASGRO software. It is a general equation that covers the lower growth rate near the threshold $\Delta K_{\text{th}}$ and the increased growth rate approaching the fracture toughness $K_{\text{crit}}$, as well as allowing for the mean stress effect by including the stress ratio $R$. The NASGRO equation is

${\frac {da}{dN}}=C\left[\left({\frac {1-f}{1-R}}\right)\Delta K\right]^{n}{\left(1-{\frac {\Delta K_{\text{th}}}{\Delta K}}\right)^{p} \over \left(1-{\frac {K_{\max }}{K_{\text{crit}}}}\right)^{q}}$

where $C$, $f$, $n$, $p$, $q$, $\Delta K_{\text{th}}$ and $K_{\text{crit}}$ are the equation coefficients.

McClintock equation

In 1967, McClintock developed an equation for the upper limit of crack growth based on the cyclic crack tip opening displacement $\Delta {\text{CTOD}}$

${da \over dN}\propto \Delta {\text{CTOD}}\approx \beta {(\Delta K)^{2} \over {2\sigma _{0}E'}}$

where $\sigma _{0}$ is the flow stress, $E'$ is the Young's modulus and $\beta$ is a constant typically in the range 0.1–0.5.

Walker equation

To account for the stress ratio effect, Walker suggested a modified form of the Paris–Erdogan equation

${da \over dN}=C{\Big (}{\overline {\Delta K}}{\Big )}^{m}=C{\bigg (}{\frac {\Delta K}{(1-R)^{1-\gamma }}}{\bigg )}^{m}=C{\big (}K_{\text{max}}(1-R)^{\gamma }{\big )}^{m}$

where, $\gamma$ is a material parameter which represents the influence of stress ratio on the fatigue crack growth rate. Typically, $\gamma$ takes a value around $0.5$, but can vary between $0.3-1.0$. In general, it is assumed that compressive portion of the loading cycle ${\big (}R<0{\big )}$ has no effect on the crack growth by considering $\gamma =0,$ which gives ${\overline {\Delta K}}=K_{\text{max}}.$ This can be physically explained by considering that the crack closes at zero load and does not behave like a crack under compressive loads. In very ductile materials like Man-Ten steel, compressive loading does contribute to the crack growth according to $\gamma =0.22$.

Elber equation

Elber modified the Paris–Erdogan equation to allow for crack closure with the introduction of the opening stress intensity level $K_{\text{op}}$ at which contact occurs. Below this level there is no movement at the crack tip and hence no growth. This effect has been used to explain the stress ratio effect and the increased rate of growth observed with short cracks. Elber's equation is

$\Delta K_{\text{eff}}=K_{\text{max}}-K_{\text{op}}$

${da \over dN}=C(\Delta K_{\text{eff}})^{m}$

Ductile and brittle materials equation

The general form of the fatigue-crack growth rate in ductile and brittle materials is given by

${da \over dN}\propto (K_{\text{max}})^{n}(\Delta K)^{p},$

where, $n$ and $p$ are material parameters. Based on different crack-advance and crack-tip shielding mechanisms in metals, ceramics, and intermetallics, it is observed that the fatigue crack growth rate in metals is significantly dependent on $\Delta K$ term, in ceramics on $K_{\text{max}}$, and intermetallics have almost similar dependence on $\Delta K$ and $K_{\text{max}}$ terms.

Prediction of fatigue life

Computer programs

There are many computer programs that implement crack growth equations such as Nasgro, AFGROW and Fastran. In addition, there are also programs that implement a probabilistic approach to crack growth that calculate the probability of failure throughout the life of a component.

Crack growth programs grow a crack from an initial flaw size until it exceeds the fracture toughness of a material and fails. Because the fracture toughness depends on the boundary conditions, the fracture toughness may change from plane strain conditions for a semi-circular surface crack to plane stress conditions for a through crack. The fracture toughness for plane stress conditions is typically twice as large as that for plane strain. However, because of the rapid rate of growth of a crack near the end of its life, variations in fracture toughness do not significantly alter the life of a component.

Crack growth programs typically provide a choice of:

• cycle counting methods to extract cycle extremes
• geometry factors that select for the shape of the crack and the applied loading
• crack growth equation
• acceleration/retardation models
• material properties such as yield strength and fracture toughness

Analytical solution

The stress intensity factor is given by

$K=\beta \sigma {\sqrt {\pi a}},$

where $\sigma$ is the applied uniform tensile stress acting on the specimen in the direction perpendicular to the crack plane, $a$ is the crack length and $\beta$ is a dimensionless parameter that depends on the geometry of the specimen. The alternating stress intensity becomes

${\begin{aligned}\Delta K&={\begin{cases}\beta (\sigma _{\text{max}}-\sigma _{\text{min}}){\sqrt {\pi a}}=\beta \Delta \sigma {\sqrt {\pi a}},\qquad R\geq 0\\\beta \sigma _{\text{max}}{\sqrt {\pi a}},\qquad R<0\end{cases}},\end{aligned}}$

where $\Delta \sigma$ is the range of the cyclic stress amplitude.

By assuming the initial crack size to be $a_{0}$, the critical crack size $a_{c}$ before the specimen fails can be computed using ${\big (}K=K_{\text{max}}=K_{\text{Ic}}{\big )}$ as

${\begin{aligned}K_{\text{Ic}}&=\beta \sigma _{\text{max}}{\sqrt {\pi a_{c}}},\\\Rightarrow a_{c}&={\frac {1}{\pi }}{\bigg (}{\frac {K_{\text{Ic}}}{\beta \sigma _{\text{max}}}}{\bigg )}^{2}.\end{aligned}}$

The above equation in $a_{c}$ is implicit in nature and can be solved numerically if necessary.

Case I

For $R\geq 0.7,$ crack closure has negligible effect on the crack growth rate and the Paris–Erdogan equation can be used to compute the fatigue life of a specimen before it reaches the critical crack size $a_{c}$ as

${\begin{aligned}{da \over dN}&=C(\Delta K)^{m}=C{\bigg (}\beta \Delta \sigma {\sqrt {\pi a}}{\bigg )}^{m},\\\Rightarrow N_{f}&={\frac {1}{({\sqrt {\pi }}\Delta \sigma )^{m}}}\int _{a_{0}}^{a_{c}}{\frac {da}{(C{\sqrt {a}}\beta )^{m}}}.\end{aligned}}$

Crack growth model with constant value of 𝛽 and R = 0

Figure 2: Geometrical representation of Center Cracked Tension test specimen

For the Griffith-Irwin crack growth model or center crack of length $2a$ in an infinite sheet as shown in the figure 2, we have $\beta =1$ and is independent of the crack length. Also, $C$ can be considered to be independent of the crack length. By assuming $\beta ={\text{constant}},$ the above integral simplifies to

$N_{f}={\frac {1}{C({\sqrt {\pi }}\beta \Delta \sigma )^{m}}}\int _{a_{0}}^{a_{c}}{\frac {da}{({\sqrt {a}})^{m}}},$

by integrating the above expression for $m\neq 2$ and $m=2$ cases, the total number of load cycles $N_{f}$ are given by

${\begin{aligned}N_{f}&={\frac {2}{(m-2)C({\sqrt {\pi }}\beta \Delta \sigma )^{m}}}{\Bigg [}{\frac {1}{(a_{0})^{\frac {m-2}{2}}}}-{\frac {1}{(a_{c})^{\frac {m-2}{2}}}}{\Bigg ]},\qquad m\neq 2,\\N_{f}&={\frac {1}{\pi C(\beta \Delta \sigma )^{2}}}\ln {\frac {a_{c}}{a_{0}}},\qquad m=2.\end{aligned}}$

Now, for $m>2$ and critical crack size to be very large in comparison to the initial crack size ${\big (}a_{c}>>a_{0}{\big )}$ will give

$N_{f}={\frac {2}{(m-2)C({\sqrt {\pi }}\Delta \sigma \beta )^{m}}}(a_{0})^{\frac {2-m}{2}}.$

The above analytical expressions for the total number of load cycles to fracture ${\big (}N_{f}{\big )}$ are obtained by assuming $Y={\text{constant}}$. For the cases, where $\beta$ is dependent on the crack size such as the Single Edge Notch Tension (SENT), Center Cracked Tension (CCT) geometries, numerical integration can be used to compute $N_{f}$.

Case II

For $R<0.7,$ crack closure phenomenon has an effect on the crack growth rate and we can invoke Walker equation to compute the fatigue life of a specimen before it reaches the critical crack size $a_{c}$ as

${\begin{aligned}{da \over dN}&=C{\bigg (}{\frac {\Delta K}{(1-R)^{1-\gamma }}}{\bigg )}^{m}={\frac {C}{(1-R)^{m(1-\gamma )}}}{\bigg (}\beta \Delta \sigma {\sqrt {\pi a}}{\bigg )}^{m},\\\Rightarrow N_{f}&={\frac {(1-R)^{m(1-\gamma )}}{({\sqrt {\pi }}\Delta \sigma )^{m}}}\int _{a_{0}}^{a_{c}}{\frac {da}{(C{\sqrt {a}}\beta )^{m}}}.\end{aligned}}$

Numerical calculation

Figure 3: Schematic representation of fatigue life prediction process

This scheme is useful when $\beta$ is dependent on the crack size $a$. The initial crack size is considered to be $a_{0}$. The stress intensity factor at the current crack size $a$ is computed using the maximum applied stress as

${\begin{aligned}K_{\text{max}}&=\beta \sigma _{\text{max}}{\sqrt {\pi a}}.\end{aligned}}$
If $K_{\text{max}}$ is less than the fracture toughness $K_{\text{Ic}}$, the crack has not reached its critical size $a_{c}$ and the simulation is continued with the current crack size to calculate the alternating stress intensity as

$\Delta K=\beta \Delta \sigma {\sqrt {\pi a}}.$

Now, by substituting the stress intensity factor in Paris–Erdogan equation, the increment in the crack size $\Delta a$ is computed as

$\Delta a=C(\Delta K)^{m}\Delta N,$

where $\Delta N$ is cycle step size. The new crack size becomes

$a_{i+1}=a_{i}+\Delta a,$

where index $i$ refers to the current iteration step. The new crack size is used to calculate the stress intensity at maximum applied stress for the next iteration. This iterative process is continued until

$K_{\text{max}}\geq K_{\text{Ic}}.$

Once this failure criterion is met, the simulation is stopped.

The schematic representation of the fatigue life prediction process is shown in figure 3.

Example

Figure 4: Geometrical representation of Single Edge Notch Tension test specimen

The stress intensity factor in a SENT specimen (see, figure 4) under fatigue crack growth is given by

${\begin{aligned}K_{I}&=\beta \sigma {\sqrt {\pi a}}=\sigma {\sqrt {\pi a}}{\Bigg [}0.265{\bigg [}1-{\frac {a}{W}}{\bigg ]}^{4}+{\frac {0.857+0.265{\frac {a}{W}}}{{\big [}1-{\frac {a}{W}}{\big ]}^{\frac {3}{2}}}}{\Bigg ]},\\\Delta K_{I}&=K_{\text{max}}-K_{\text{min}}=\beta \Delta \sigma {\sqrt {\pi a}}.\end{aligned}}$

The following parameters are considered for the calculation

$a_{0}=5$ mm, $W=100$ mm, $h=200$ mm, $K_{\text{Ic}}=30{\text{ MPa}}{\sqrt {\text{m}}}$, $R={\frac {K_{\text{min}}}{K_{\text{max}}}}=0.7$,

$\Delta \sigma =20$MPa,$C=4.6774\times 10^{-11}{\frac {\text{m}}{\text{cycle}}}{\frac {1}{({\text{MPa}}{\sqrt {\text{m}}})^{m}}}$, $m=3.874$.

The critical crack length, $a=a_{c}$, can be computed when $K_{\text{max}}=K_{\text{Ic}}$ as

$a_{c}={\frac {1}{\pi }}{\Bigg (}{\frac {0.45}{\beta }}{\Bigg )}^{2}.$

By solving the above equation, the critical crack length is obtained as $a_{c}=26.7{\text{mm}}$.

Now, invoking the Paris–Erdogan equation gives

$N_{f}={\frac {1}{C(\Delta \sigma )^{m}({\sqrt {\pi }})^{m}}}\int _{a_{0}}^{a_{c}}{\frac {da}{a^{\frac {m}{2}}{\Bigg [}0.265{\bigg [}1-{\frac {a}{W}}{\bigg ]}^{4}+{\frac {0.857+0.265{\frac {a}{W}}}{{\big [}1-{\frac {a}{W}}{\big ]}^{\frac {3}{2}}}}{\Bigg ]}^{m}}}$

By numerical integration of the above expression, the total number of load cycles to failure is obtained as $N_{f}=1.2085\times 10^{6}{\text{ cycles}}$.

External links

• Forman, R. G.; Shivakumar, V.; Cardinal, J. W.; Williams, L. C.; McKeighan, P. C. (2005). "Fatigue Crack Growth Database for Damage Tolerance Analysis" (PDF). FAA. Retrieved 6 July 2019.
• Gallagher, J. P.; Giessler, F. J.; Berens, A. P.; Engle, Jr, J. M. "USAF Damage Tolerant Design Handbook: Guidelines for the Analysis and Design of Damage Tolerant Aircraft Structures. Revision B". Archived from the original on 9 July 2019. Retrieved 9 July 2019.
• "Damage Tolerance Assessment Handbook Volume I: Introduction, Fracture Mechanics, Fatigue Crack Propagation" (PDF). Federal Aviation Administration. 1993. Retrieved 16 July 2019.