fatigue failure through bending david burnette me 498
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![Page 1: Fatigue Failure Through Bending David Burnette ME 498](https://reader031.vdocuments.us/reader031/viewer/2022032704/56649d4d5503460f94a2bcc2/html5/thumbnails/1.jpg)
Fatigue Failure Through BendingDavid Burnette
ME 498
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Overview
• Objectives of experiment
• Importance and theory
• Experimental details
• Result
• Conclusions and recommendations
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Objectives
• To become familiar with fatigue testing procedures
• Develop fatigue data for AA 6061-T6 specimens
• Extrapolate the endurance limit from the S-N curve (at 5x10^8 cycles)
• Compare estimated endurance limit and cycles to failure to known
• Evaluate the surface characteristics of fatigue failure
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What is Fatigue?
Crack Propagation
Examples of Fatigue Factors
• Size, loading types• Stress concentration factors• temperature, corrosion
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125.7 mm
Applied load + self loading weight
Bearing
Cantilever arm
ø5.00
Set screw b = 1257. P r
I (N/mm2)
I = d4
64
N
aapplied b
1
a ultimate
endurance
0 81 2.
endurance
ultimate9.0log
X
1b
]Nlog[2
1X reference
Desired Stress Stress
(MPa)
Required Load
(g)
.9 247.5 2337.7
.8 220 2190
.7 192.5 1916
.6 165 1641
Testing Procedures - Application of Stresses
y
y
y
y
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Test Specimens – Cycles to Failure Comparison
Aluminum Alloys:Nearly pure (>95%), precipitation hardening, tempering, lack of carbon
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Experimental Setup
1
2
3
4
DC
B A
Cantilever Arm
6061-T6 specimen
Motor
LOAD Bending Stress
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Results
• Endurance limit for 6061-T6 alloy at 5x108
• Predicted Cycles to Failure v. Observed
• Fracture Surface
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Results - Chauvenet
N d/σ5 1.656 1.737 1.818 1.869 1.9110 1.9612 2.0414 2.1016 2.1518 2.2020 2.24
1 data point removed with Chauvenet’s:
D=σ *(d/σ)
Stress Allowed Deviation (cycles)
.9 46659
.8 142573
.7 331482
.6 1367672
y
y
y
y
y
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Load (kg) Stress (MPa) Mean Cycles Predicted % Difference 2.34 247.5 45423 67900 33.1 2.19 220 124550 203000 38.6 1.92 192.5 389750 702000 44.5 1.64 165 1269375 2940000 56.8
Results - Predicted Cycles
Causes of Error
eccentricity (set screw), yield strength, diameter, number of points (12)
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Fatigue Failure for AA 6061-T6
y = -0.1147x + 8.927
R2 = 0.9998
8.10
8.15
8.20
8.25
8.30
8.35
8.40
8.45
2.0000 3.0000 4.0000 5.0000 6.0000 7.0000
Log (Cycles to Failure)
Log
(A
ppli
ed s
tres
s)
σe = 85 MPa
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Results - Diameter Uncertainty
I = d4
64
Radius
(mm)
Endurance limit(at 5x10^8 cycles)
Difference from published values
2.50 85 MPa 10.5%
2.45 89 MPa 6.3%
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Results - Surface conditions
• Fatigue failure versus dynamic failure
• Crack Propagation
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Conclusions• Fatigue failure is very different than static Fatigue failure is very different than static or dynamic failuresor dynamic failures
• A small change in diameter can A small change in diameter can significantly increase the stresssignificantly increase the stress
• Wide range of deviations (Factor of Safety)Wide range of deviations (Factor of Safety)
• Difference of only 10.5% with eccentricity Difference of only 10.5% with eccentricity (human error), diameter uncertainty, alloy (human error), diameter uncertainty, alloy uncertainty, etcuncertainty, etc
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Recommendations
• Replace set screws with chuck or threaded specimens
• Increase size of aluminum specimens (fewer points)