Development of Life Prediction Models for High Strength Steel in a Hydrogen Emitting Environment
Solvent substitution for maintenance and overhaul operations of military systems has been a primary environmental concern for many years. Cadmium replacement in these systems has been targeted for decades. Both of these areas have a common obstacle for implementation of any potential alternate. Hydrogen embrittlement of high strength steel is the most predominant unforeseen hurdle since high strength materials show sensitivity to the phenomena and the source of the hydrogen can be anything within the fabrication process, maintenance practice or the natural corrosion cycle. Standardized testing on this issue has traditionally stemmed from the aerospace industry where it is a principal focus.
#plating #masking #aerospace
by Scott M. Grendahl, U.S. Army Research Laboratory Aberdeen Proving Ground; and Ed Babcock, Stephen Gaydos and Joseph Osborne, the Boeing Co.
Solvent substitution for maintenance and overhaul operations of military systems has been a primary environmental concern for many years. Cadmium replacement in these systems has been targeted for decades. Both of these areas have a common obstacle for implementation of any potential alternate. Hydrogen embrittlement of high strength steel is the most predominant unforeseen hurdle since high strength materials show sensitivity to the phenomena and the source of the hydrogen can be anything within the fabrication process, maintenance practice or the natural corrosion cycle. Standardized testing on this issue has traditionally stemmed from the aerospace industry where it is a principal focus.
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A design of experiment (DOE) approach was used over a range of material strength for both airmelted (AMS 6415) and aerospace grade (AMS 6414) 4340 steel, load level and hydrogen environment. Five ASTM F519 geometries were explored while monitoring load levels to determine a precise time to fracture at a specific notch fracture strength (NFS), material strength and hydrogen emitting environment (NaCl solution). This allowed comparisons across geometry and material to be drawn. Incorporating the failure time, load and stress levels into the failure models yielded predictive equations over broad parameter ranges. Reliable predictions of hydrogen sensitivity under specific conditions were then realized.
Ultimately, this work aims at evaluating the most prospective environmentallyfriendly maintenance chemicals and cadmium alternative coatings that have their use limited by the perceived risk of hydrogen embrittlement. In subsequent years, this work will evaluate the prospective chemicals and coatings over a range of material strength, load level and hydrogen emitting environment which will demonstrate hydrogen sensitivity over parameter ranges, while developing life prediction models for each case. This should greatly increase the applications for which the replacements will be considered, as the models provide the acceptability criteria for the parameters specific to each application.
Keywords: Hydrogen embrittlement testing, hydrogen embrittlement prediction, high strength steels.
• T2 = 158 ± 5 ksi (153163 ksi)
• T3 = 210 ± 5 ksi (205215 ksi)
• T4 = 262 ± 5 ksi (257267 ksi)
• T5 = 280 ± 5 ksi (275285 ksi)
• T2 = 75 + 6 tensiles
• T3 = 180 + 6 tensiles
• T4 = 75 + 6 tensiles
• T5 = 45 + 6 tensiles
Table 1  Temper lot quantities.
Temper Lot No.  Strength Target, ksi  No. of specimens  
1a.1  1a.2  1c  1d  1e  Total  +  Tensiles  
T1  140  6  6  6  6  6  30  +  6 
T2  158  15  15  15  15  15  75  +  6 
T3  210  36  36  36  36  36  180  +  6 
T4  262  15  15  15  15  15  75  +  6 
T5  280  9  9  9  9  9  45  +  6 
Condition  α  Ì¶  0  +  +α 
Strength, ksi  140  158  210  262  280 
Test load, %NFS  40  45  60  75  95 
NaCl, wt%  1.25E05  0.01  0.50  2.36  3.50 
The design of experiment approach was refined with preliminary ruggedness and risk reduction efforts at Boeing Mesa, with technical assistance from Boeing St. Louis, Seattle, and ARL. Typical of DoEs, it consisted of three test portions, a linear portion, a quadratic portion and a confirmation portion. The example matrix is as presented in Tables 3 thru 5 with the condition values corresponding to Table 2. These experiments aided the development of appropriate boundary conditions for the larger effort.
Repeat entire matrix 2× for 1a.1, 1a.2, 1c, 1d and 1e  Run ID  A  B  C  Run order 
Strength, ksi  Test load, %NFS  NaCl, wt%  
Linear portion  L1  Ì¶  Ì¶  Ì¶  Random 
L2  Ì¶  Ì¶  +  
L3  Ì¶  +  Ì¶  
L4  Ì¶  +  +  
L5  +  Ì¶  Ì¶  
L6  +  Ì¶  +  
L7  +  +  Ì¶  
L8  +  +  +  
Center points  C1  0  0  0  
C2  0  0  0  
C3  0  0  0  
C4  0  0  0  
C5  0  0  0  
C6  0  0  0 
Repeat Q1Q6 5× for 1a.1, 1a.2, 1c, 1d and 1e  Run ID  A  B  C  Run order 
Strength, ksi  Test load, %NFS  NaCl, wt%  
Not replicated  C7  0  0  0  First 
Quadratic portion  Q1  +α  0  0  Random 
Q2  α  0  0  
Q3  0  +α  0  
Q4  0  α  0  
Q5  0  0  +α  
Q6  0  0  α  
Not replicated  C8  0  0  0  Last 
 Run ID  A  B  C  Run order 
Strength, ksi  Test load, %NFS  NaCl, wt%  
Confirmation portion  1  Varied, depending on outcome of Linear, Center and Quadratic Results  Random  
2  
3  
4  
5  
6  
7  
8  
9  
10  
11  
12  
13  
14  
15  
16 
After the linear and center point data runs were completed, initial calculations were made for the predictive model equations. Those initial models were utilized to choose confirmation runs to be researched. The confirmation run results were then incorporated into refining the initial working model.
As stated previously, upon conclusion of the linear, center and quadratic test runs, preliminary life prediction models were created. These models were then used in the confirmation test portion of the matrix to choose appropriate parameters to both enhance and verify the model. Final life prediction equations and three dimensional models were created after the incorporation of the confirmation data.
Airmelted SAEAMS6415 steel
1a.1 Preliminary Model
where
Offset = σ×ln(ln(1P)) (4a)
for which
T = time to event. It is either the time to failure or the time to the end of the experiment (168 hr).
P = the predicted percentile. At a P of 70%, 70% of the failures would be above the curve and 30% would fall below the curve generated.
σ = 1/Weibull shape parameter. Weibull shape parameter = 0.579.
 A negative value of the coefficient is indicative of a shorter lifetime as the variable increases.
 Weibull shape < 1 → hazard rate (failure rate) decreases as time increases.
 Infant mortality. After initial early failures the survival improves with age.
1a.1 Confirmation Model
ln(T) = 6.774.98×Str1.29×Load0.93×NaCl3.66×Str×Load+Offset (5)
Weibull shape parameter = 0.567
1a.2 Preliminary Model
ln(T) = 9.095.49×Str7.39×Load1.39×NaCl+Offset (6)
Weibull shape parameter = 0.377
1a.2 Confirmation Model
ln(T) = 8.755.90×Str6.53×Load1.33×NaCl+Offset (7)
Weibull shape parameter = 0.397
1c Preliminary Model
ln(T) = 19.0111.67×Str9.93×Load0.88×NaCl+Offset (8)
Weibull shape parameter = 0.343
1c Confirmation Model
ln(T) = 20.9110.53×Str11.30×Load1.25×NaCl+Offset (9)
Weibull shape parameter = 0.278
1d Preliminary Model
ln(T) = 7.834.04×Str3.54×Load1.01×NaCl+Offset (10)
Weibull shape parameter = 0.515
1d Confirmation Model
ln(T) = 7.684.12×Str3.08×Load6.04×NaCl+Offset (11)
Weibull shape parameter = 0.546
1e Preliminary Model
ln(T) = 12.317.45×Str6.45×Load0.97×NaCl+Offset (12)
Weibull shape parameter = 0.505
1e Confirmation Model
ln(T) = 13.148.16×Str6.58×Load0.73×NaCl+Offset (13)
Weibull shape parameter = 0.493
Vacuum Arc Remelted SAEAMS6414 steel
1a.1 Preliminary Model
ln(T) = 5.204.79×Str2.22×Load1.73×NaCl1.24×Str×Str+Offset (14)
Weibull shape parameter = 1.090
1a.1 Confirmation Model
ln(T) = 5.665.28×Str2.82×Load1.52×NaCl1.29×Str×Str+Offset (15)
Weibull shape parameter = 0.913
1a.2 Preliminary Model
ln(T) = 7.905.20×Str3.00×Load1.77×NaCl+Offset (16)
Weibull shape parameter = 0.643
1a.2 Confirmation Model
ln(T) = 7.697.73×Str2.93×Load1.57×NaCl2.40×Str×Str+Offset (17)
Weibull shape parameter = 0.644
1c Preliminary Model
ln(T) = 11.358.27×Str5.96×Load3.2×NaCl2.5×Str×Str+Offset (18)
Weibull shape parameter = 0.548
1c Confirmation Model
ln(T) = 11.68.19×Str6.49×Load2.92×NaCl2.34×Str×Str+Offset (19)
Weibull shape parameter = 0.541
1d Preliminary Model
ln(T) = 6.636.85×Str1.40×Load0.95×NaCl2.80×Str×Str+Offset (20)
Weibull shape parameter = 1.234
1d Confirmation Model
ln(T) = 6.526.58×Str1.08×Load0.99×NaCl2.60×Str×Str+Offset (21)
Weibull shape parameter = 1.237
1e Preliminary Model
ln(T) = 9.0811.04×Str1.68×Load2.21×NaCl4.29×Str×Str+Offset (22)
Weibull shape parameter = 0.646
1e Confirmation Model
ln(T) = 8.929.56×Str1.93×Load2.18×NaCl3.26×Str×Str+Offset (23)
Weibull shape parameter = 0.695
 Life prediction models were developed that accurately represent the expected hydrogen sensitivity over the range of parameters explored for airmelted and vacuum arc remelted 4340 steel.
 The trends observed in the data were reasonably consistent across all test geometries. Sensitivity increases with applied load, material strength and to a lesser degree NaCl concentration.
 Applied stress has the most direct effect on hydrogen sensitivity, while material strength is a close second. Increasing the value of either parameter directly heightens the sensitivity to hydrogen.
 4340 steel does not appear susceptible to hydrogen absorbed from environmental corrosion below the 160 ksi strength level.
 High residual stress levels (4050% of UTS) are capable of causing hydrogen embrittlement without further applied system stresses.
 The 1d test geometry proved the most sensitive to hydrogen and also conducive to testing multiple specimens in various environments without requiring test load frames.
 Vacuum arc remelted steel was more susceptible to hydrogen than airmelted 4340 steel in this environment.
 Vacuum arc remelted steel was more sensitive to NaCl concentration than airmelted 4340 steel.
 SAEAMS 6415S2007, Steel, Bars, Forgings, and Tubing 0.80 Cr  1.8 Ni  0.25 Mo (0.38  0.43 C), SAE World Headquarters, Warrendale, PA, 2007.
 SAEAMS 6414K2007, Steel, Bars, Forgings, and Tubing 0.80 Cr  1.8 Ni  0.25 Mo (0.38  0.43 C) (SAE 4340) Vacuum Consumable Electrode Remelted, SAE World Headquarters, Warrendale, PA, 2007.
 ASTM F51910, Standard Test Method for Mechanical Hydrogen Embrittlement Evaluation of Plating/Coating Processes and Service Environments, ASTM International, West Conshohocken, PA, 2010.
 MILSTD870C, Department of Defense Standard Practice: Cadmium Plating, Low Embrittlement, ElectroDeposition, 2009.
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