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Marin Endurance Limit Equations and Calculator
Machine Design Applications
Strength and Mechanics of Materials
Marin Endurance Limit Equations and Calculator
Marin Factors for Corrected Endurance Limit Fatigue
The endurance limit (S'_{e}) determined using Eq. 2 that is established from fatigue tests on a standard test specimen must be modified for factors that will usually be different for an actual machine element. These factors account for differences in surface finish, size, load type, temperature, and other miscellaneous effects that may differ from those for the test specimen.
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The mathematical model commonly used to apply these factors is credited to Joseph Marin (1962) and is given as:
Eq. 1
S_{e} = k_{a} k_{b} k_{c} k_{d} k_{e} S'_{e}
Endurance Limit. A sufficient number of ferrous materials (carbon steels, alloy steels, and wrought irons) have been tested using the R. R. Moore rotatingbeam machine so that the following relationship between the ultimate tensile strength (Sut ) and the endurance limit (Se ) that would have been obtained from a fatigue test can be assumed to give an accurate value even if the material has not been tested. This relationship is given in Eq. (2) for both the U.S. Customary and SI/metric system of units.
Eq. 2
U.S. Customary: S'_{e} =  0.504 S_{ut}  S_{ut} ≤ 200kpsi 
100 kpsi  S_{ut} > 200 kpsi 
SI/metric: S'_{e} =  0.504 S_{ut}  S_{ut} ≤ 1400 MPa 
700 MPa  S_{ut} > 1400 MPa 
Where:
S_{e} = endurance limit corrected so that it can predict fatigue resistance in a real component
S'_{e} = endurance limit obtained from guidelines from R.R. Moore test
S_{ut} = Endurance Limit
k_{a} = surface finish factor
k_{b} = size factor
k_{c} = load type factor
k_{d} = temperature factor
k_{} = miscellaneous effects factor
Each of these five factors are used to provide an estimate of the endurance limit (Se) for a particular machine element design.
The first factor to discuss is the surface finish factor (k_{a}), probably the most important of the five factors.
Surface Finish Factor k_{a}
The surface finish of the R. R. Moore rotatingbeam machine test specimen is highly polished, particularly to remove any circumferential scratches or marks that would cause premature failure and thereby corrupt the data. The actual machine element under investigation may have a relatively rough surface finish, thereby providing a place for a crack to develop, eventually leading to a fatigue failure.
Eq. 3
k_{a} = a S^{b}_{ut}
Where:
Coefficient a has units of stress abd exponent (b), which is negative and dimensionless is found below:
Surface finish 
Factor a 
Exponent b 

kpsi 
Mpa 

Ground 
1.34 
1.58 
0.085 
Machined 
2.70 
4.51 
0.265 
Colddrawn 
2.70 
4.51 
0.265 
Hotrolled 
14.4 
57.7 
0.718 
As Forged 
39.9 
272 
0.995 
Ultimate Tensile Strength S_{ut}
Surface finish 
kpsi 
Mpa 
Surface factor k_{a} 
Machined 
65 
455 
0.89 
As forged 
65 
455 
0.63 
Machined 
125 
875 
0.75 
As forged 
125 
875 
0.33 
Size Factor k_{b}
The size factor k_{b} accounts for the difference between the machine element and the test specimen. For axial loading, the size factor (kb) is not an issue, so use the following value:
k_{b} = 1
For bending or torsion, use the following relationships for the range of sizes
Eq. 4
k_{b} =  (d / 0.3)^{0.1133}  0.11 in ≤ d ≤ 2 in 
(d / 7.62)^{0.1133}  2.79mm ≤ d ≤ 51 mm 
For bending and torsion of larger sizes, the size factor (k_{b}) varies between 0.60 and 0.75. For machine elements that are round but not rotating, or shapes that are not round, an effective diameter, denoted (d_{e}), must be used in Eq. (4).
For a nonrotating round or hollow cross section, the effective diameter (d_{e}) is given in Eq.
Eq 5
d_{e} = 0.370 D
where the diameter (D) is the outside diameter of either the solid or hollow cross section.
For a rectangular cross section (b × h), the effective diameter (d_{e}) is given in Eq. (5) as:
Eq. 6
d_{e} = 0.808 (bh)^{1/2}
Temperature Factor k_{d}.
For temperatures very much lower than room temperature materials like ductile steel become brittle. Materials like aluminum seem to be unaffected by similar low temperatures.
Eq. 7
k_{d} = S_{T} / S_{RT}
where ( S_{T} ) is the ultimate tensile strength at some specific temperature ( T ) and ( S_{RT} ) is the ultimate tensile strength at room temperature (RT).
Temperature Factors
TABLE 6 Temperature Factors
◦F 
kd 
◦C 
kd 
70 
1.000 
20 
1.000 
100 
1.008 
50 
1.010 
200 
1.020 
100 
1.020 
300 
1.024 
150 
1.025 
400 
1.018 
200 
1.020 
500 
0.995 
250 
1.000 
600 
0.963 
300 
0.975 
700 
0.927 
350 
0.927 
800 
0.872 
400 
0.922 
900 
0.797 
450 
0.840 
1000 
0.698 
500 
0.766 
1100 
0.567 
550 
0.670 
Miscellaneous Effects Factor. All the following effects are important in the dynamic loading of machine elements, however, only one can be quantified. These effects are residual stresses, corrosion, electrolytic plating, metal spraying, cyclic frequency, frettage corrosion, and stress concentration.
Residual stresses can improve the endurance limit if they increase the compressive stresses, especially at the surface through such processes as shot peening and most cold working. However, residual stresses that increase the tensile stresses, again especially at the surface, tend to reduce the endurance limit.
Corrosion tends to reduce the endurance limit as it produces imperfections at the surface of the machine element where the small cracks associated with fatigue failure can develop.
Electrolytic plating such as chromium or cadmium plating can reduce the endurance limit by as much as 50 percent.
Like corrosion, metal spraying produces imperfections at the surface so it tends to reduce the endurance limit.
Cyclic frequency is usually not important, unless the temperature is relatively high and there is the presence of corrosion. The lower the frequency of the repeated reversed loading and the higher the temperature, the faster the propagation of cracks once they develop, and therefore, the shorter the fatigue life of the machine element.
Frettage is a type of corrosion where very tightly fitted parts (bolted and riveted joints, press or fits between gears, pulleys, and shafts, and bearing races in close tolerance seats) move ever so slightly producing pitting and discoloration similar to normal corrosion. The result is a reduced fatigue life because small cracks can develop in these microscopic areas. Depending on the material, frettage corrosion can reduce the fatigue life from 10 to 80 percent, so it is an important issue to consider.
Stress concentration is the only miscellaneous effect that can be accurately quantified.
Reduced stress concentration factor ( K_{f} ) needed to be applied to the design of brittle materials. As fatigue failure is similar to brittle failure, stress concentrations need to be considered for both ductile and brittle materials under repeated loadings, whether they are completely reversed or fluctuating.
Reduced stress concentration factor ( K_{f} ) was determined from equation:
K_{f} = 1 + q (Kt  1 )
where the geometric stress concentration factor ( K_{t} ) is modified or reduced due to any notch sensitivity (q) of the material. Values for the stress concentration factor ( K_{t} ) for various types of geometric discontinuities are given in any number of references.
The miscellaneous effects factor for stress concentration ( k_{e} ) is therefore the reciprocal of the reduced stress concentration factor ( K_{f} ) and given
k_{e} = 1 / K_{f}
Where as ( K_{f} ) is usually greater than one, the miscellaneous effects factor ( k_{e} ) will be less than 1 and thereby reduce the test specimen endurance limit ( S'_{e} ) accordingly.
Note that the miscellaneous effects factor ( k_{e} ) for stress concentration applies to the endurance limit ( S'_{e} ) at (N =10^{6}) and greater. However, below (N =10^{3}) cycles it has no effect, meaning (K_{f} = 1) or (k_{e} = 1). Similar to the process for finite life, between (N =10^{3}) and (N =10^{6}) cycles define a modified stress concentration factor ( K'_{f} ) where:
K'_{f} = a N^{b}
and the coefficients (a) and (b), both dimensionless, are given:
a = 1 / K_{f}
Related:
 Strength of Materials Belyaev
 Modes of Fatigue Failure
 Fatigue Crack Growth Analysis Review
 Fatigue  Strength ( Mechanics ) of Materials
 Metal Fatigue Engineering Analysis Excel Spreadsheet Calculator
 Fatigue and Machine Design Excel Spreadsheet Calculator
Source:
Marks' Calculations for Machine Design,
Thomas H. Brown, Jr. Ph.D., PE
Faculty Associate
Institute for Transportation Research and Education
NC State University
Raleigh, North Carolina