2. Nature of fatigue failure
Starts with a crack
Usually at a stress concentration
Crack propagates until the material fractures
suddenly
Fatigue failure is typically sudden and
complete, and doesn’t give warning
11. Fatigue
Fatigue strength and endurance limit
Estimating FS and EL
Modifying factors
Thus far we’ve studied static failure of machine elements
The second major class of component failure is due to dynamic loading
Variable stresses
Repeated stresses
Alternating stresses
Fluctuating stresses
The ultimate strength of a material (Su) is the maximum stress a
material can sustain before failure assuming the load is applied only
once and held
A material can also fail by being loaded repeatedly to a stress level that
is LESS than Su
Fatigue failure
12. Approach to fatigue failure in analysis and design
Fatigue-life methods (6-3 to 6-6)
Stress Life Method (Used in this course)
Strain Life Method
Linear Elastic Fracture Mechanics Method
Stress-life method (rest of chapter 6)
Addresses high cycle Fatigue (>103 ) Well
Not Accurate for Low Cycle Fatigue (<103)
13. The 3 major methods
Stress-life
Based on stress levels only
Least accurate for low-cycle fatigue
Most traditional
Easiest to implement
Ample supporting data
Represents high-cycle applications adequately
Strain-life
More detailed analysis of plastic deformation at localized regions
Good for low-cycle fatigue applications
Some uncertainties exist in the results
Linear-elastic fracture mechanics
Assumes crack is already present and detected
Predicts crack growth with respect to stress intensity
Practical when applied to large structures in conjunction with computer
codes and periodic inspection
14. Fatigue analysis
2 primary classifications of
fatigue
Alternating – no DC component
Fluctuating – non-zero DC
component
15. Analysis of alternating stresses
As the number of cycles
increases, the fatigue strength
Sf (the point of failure due to
fatigue loading) decreases
For steel and titanium, this
fatigue strength is never less
than the endurance limit, Se
Our design criteria is:
As the number of cycles
approaches infinity (N ∞),
Sf(N) = Se (for iron or Steel)
a
f N
S
)
(
16. Method of calculating fatigue strength
Seems like we should be able to use graphs
like this to calculate our fatigue strength if
we know the material and the number of
cycles
We could use our factor of safety equation
as our design equation
But there are a couple of problems with this
approach
S-N information is difficult to obtain and thus is
much more scarce than -e information
S-N diagram is created for a lab specimen
Smooth
Circular
Ideal conditions
Therefore, we need analytical methods for
estimating Sf(N) and Se
a
f N
S
)
(
17. Terminology and notation
Infinite life versus finite life
Infinite life
Implies N ∞
Use endurance limit (Se) of material
Lowest value for strength
Finite life
Implies we know a value of N (number of cycles)
Use fatigue strength (Sf) of the material (higher than Se)
Prime (‘) versus no prime
Strength variable with a ‘ (Se’)
Implies that the value of that strength (endurance limit) applies to a LAB SPECIMEN in
controlled conditions
Variables without a ‘ (Se, Sf)
Implies that the value of that strength applies to an actual case
First we find the prime value for our situation (Se’)
Then we will modify this value to account for differences between a lab specimen and our
actual situation
This will give us Se (depending on whether we are considering infinite life or finite life)
Note that our design equation uses Sf, so we won’t be able to account for safety factors until
we have calculated Se’ and Se
a
f N
S
)
(
a
e
S
18. Estimating Se’ – Steel and Iron
For steels and irons, we can estimate the endurance limit (Se’)
based on the ultimate strength of the material (Sut)
Steel
Se’ = 0.5 Sut for Sut < 200 ksi (1400 MPa)
= 100 ksi (700 MPa) for all other values of Sut
Iron
Se’ = 0.4(min Sut)f/ gray cast Iron Sut<60 ksi(400MPa)
= 24 ksi (160 MPa) for all other values of Sut
Note: ASTM # for gray cast iron is the min Sut
19. S-N Plot with Endurance Limit
a
e
S
a
f N
S
)
(
a
e
S
20. Estimating Se’ – Aluminum and Copper
Alloys
For aluminum and copper alloys, there is no endurance limit
Eventually, these materials will fail due to repeated loading
To come up with an “equivalent” endurance limit, designers
typically use the value of the fatigue strength (Sf’) at 108 cycles
Aluminum alloys
Se’ (Sf at 108 cycles) = 0.4 Sut for Sut < 48 ksi (330 MPa)
= 19 ksi (130 MPa) for all other values of Sut
Copper alloys
Se’ (Sf at 108 cycles) = 0.4 Sut for Sut < 35 ksi (250 MPa)
= 14 ksi (100 MPa) for all other values of Sut
21. Correction factors
Now we have Se’ (infinite life)
We need to account for differences between the lab specimen and a real
specimen (material, manufacturing, environment, design)
We use correction factors
Strength reduction factors
Marin modification factors
These will account for differences between an ideal lab specimen and real life
Se = ka kb kc kd ke kf Se’
ka – surface factor
kb – size factor
kc – load factor
kd – temperature factor
ke – reliability factor
Kf – miscellaneous-effects factor
Modification factors have been found empirically and are described in section 6-9 of
Shigley-Mischke-Budynas (see examples)
If calculating fatigue strength for finite life, (Sf), use equations on previous slide
22. Endurance limit modifying factors
Surface (ka)
Accounts for different surface finishes
Ground, machined, cold-drawn, hot-rolled, as-forged
Size (kb)
Different factors depending on loading
Bending and torsion (see pg. 280)
Axial (kb = 1)
Loading (kc)
Endurance limits differ with Sut based on fatigue loading (bending, axial, torsion)
Temperature (kd)
Accounts for effects of operating temperature (Not significant factor for T<250 C [482 F])
Reliability (ke)
Accounts for scatter of data from actual test results (note ke=1 gives only a 50% reliability)
Miscellaneous-effects (kf)
Accounts for reduction in endurance limit due to all other effects
Reminder that these must be accounted for
Residual stresses
Corrosion
etc
28. Stress concentration (SC) and fatigue failure
Unlike with static loading, both ductile and
brittle materials are significantly affected by
stress concentrations for repeated loading
cases
We use stress concentration factors to modify
the nominal stress
SC factor is different for ductile and brittle
materials
29. SC factor – fatigue
= kfnom+ = kfo
t = kfstnom = kfsto
kf is a reduced value of kT and o is the nominal
stress.
kf called fatigue stress concentration factor
Why reduced? Some materials are not fully sensitive
to the presence of notches (SC’s) therefore,
depending on the material, we reduce the effect of
the SC
30. Fatigue SC factor
kf = [1 + q(kt – 1)]
kfs = [1 + qshear(kts – 1)]
kt or kts and nominal stresses
Table A-15 & 16 (pages 1006-1013 in Appendix)
q and qshear
Notch sensitivity factor
Find using figures 6-20 and 6-21 in book (Shigley) for steels
and aluminums
Use q = 0.20 for cast iron
Brittle materials have low sensitivity to notches
As kf approaches kt, q increasing (sensitivity to notches, SC’s)
If kf ~ 1, insensitive (q = 0)
Property of the material
31. Example
AISI 1020 as-rolled steel
Machined finish
Find Fmax for:
= 1.8
Infinite life
Design Equation:
= Se / ’
Se because infinite life
32. Example, cont.
= Se / ’
What do we need?
Se
’
Considerations?
Infinite life, steel
Modification factors
Stress concentration (hole)
Find ’nom (without SC)
F
F
h
d
b
P
A
P
nom 2083
10
12
60
-
-
33. Example, cont.
Now add SC factor:
From Fig. 6-20,
r = 6 mm
Sut = 448 MPa = 65.0 ksi
q ~ 0.8
nom
t
nom
f k
q
k
-
1
1
34. Example, cont.
From Fig. A-15-1,
Unloaded hole
d/b = 12/60 = 0.2
kt ~ 2.5
q = 0.8
kt = 2.5
’nom = 2083 F
F
F
k
q nom
t
4583
2083
1
5
.
2
8
.
0
1
1
1
-
-
35. Example, cont.
Now, estimate Se
Steel:
Se’ = 0.5 Sut for Sut < 1400 MPa (eqn. 6-8)
700 MPa else
AISI 1020 As-rolled
Sut = 448 MPa
Se’ = 0.50(448) = 224 MPa