Representing crack growth in additively manufactured Ti-6Al-4V

Jones, Rhys; Michopoulos, John G.; Iliopoulos, Athanasios; Phan, Nam; Nguyen, T. H.

doi:10.1016/j.ijfatigue.2018.07.019

Cited by 62 publications

(77 citation statements)

References 31 publications

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“…The expression presented by Equation (5) can be plotted to provide a visual depiction of the goodness-of-fit associated with the various instances Equation (2). In this section, we first show that the AM Ti-6Al-4V crack growth data presented in [35][36][37], which were not studied in [17], also conform to Equation (3).…”

Section: Crack Growth In Additively Manufactured Ti-6al-4vmentioning

confidence: 97%

“…While AM offers the potential to economically fabricate customized parts with complex geometries, Reference [31] explained that the mechanical behavior of these materials must be better understood (related statements can be found in the US Federal Aviation Administration review paper [32], as well as in [17,33]) before AM can be utilized for critical load-bearing applications. This is particularly true for aircraft applications where, as detailed in MIL-STD 1530 [34], the design and certification approval requires analytical tools that are capable of modelling crack growth.…”

Section: Crack Growth In Additively Manufactured Ti-6al-4vmentioning

confidence: 99%

“…Here we see that these three different studies yielded similar / versus ΔK data. It would therefore be expected that the Boeing India / versus ∆ curves could again be represented as per [4,17] Equation (4) was again used through a global optimization scheme to compute these curves. The identified values of ∆K thr and A are given in Table 2.…”

Section: Boeing India Crack Growth Datamentioning

confidence: 99%

“…[2,5,10,13,16]. Furthermore, to the best of the authors' knowledge, Equation (2) is the only form of the NASGRO equation that has been shown to capture crack growth in AM Ti-6Al-4V fabricated in a wide range of AM processes [17]. With this in mind, and since if AM is to be used for replacement parts on operational aircraft the ability to assess the parts' performance under operational flight loads is essential, this paper focuses on the use of Equation (2) to represent crack growth in a range of AM materials.…”

Section: Introductionmentioning

confidence: 99%

“…Consequently, the present paper focuses on the ability of Equation (2) to model crack growth in AM Ti-6Al-4V, AM 316L stainless steel and AM AerMet100 steel. To this end, the present paper builds on the authors' prior work [17] where it was shown that, regardless of whether the AM process is:…”

mentioning

confidence: 99%

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Crack Growth in a Range of Additively Manufactured Aerospace Structural Materials

et al. 2018

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The aerospace industry is now beginning to adopt Additive Manufacturing (AM), both for new aircraft design and to help improve aircraft availability (aircraft sustainment). However, MIL-STD 1530 highlights that to certify airworthiness, the operational life of the airframe must be determined by a damage tolerance analysis. MIL-STD 1530 also states that in this process, the role of testing is merely to validate or correct the analysis. Consequently, if AM-produced parts are to be used as load-carrying members, it is important that the d a / d N versus ΔK curves be determined and, if possible, a valid mathematical representation determined. The present paper demonstrates that for AM Ti-6Al-4V, AM 316L stainless steel, and AM AerMet 100 steel, the d a / d N versus ΔK curves can be represented reasonably well by the Hartman-Schijve variant of the NASGRO crack growth equation. It is also shown that the variability in the various AM d a / d N versus Δ K curves is captured reasonably well by using the curve determined for conventionally manufactured materials and allowing for changes in the threshold and the cyclic fracture toughness terms.

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Section: Crack Growth In Additively Manufactured Ti-6al-4vmentioning

confidence: 97%

Section: Crack Growth In Additively Manufactured Ti-6al-4vmentioning

confidence: 99%

Section: Boeing India Crack Growth Datamentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Crack Growth in a Range of Additively Manufactured Aerospace Structural Materials

et al. 2018

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Combined effect of both surface finish and sub‐surface porosity on component strength under repeated load conditions

McMillan

Jones

2020

Engineering Reports

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High duty engineering component life is usually demonstrated through extensive testing and statistical analysis applied to empirical curve-fit equations. Because of this, the extent of the testing required is huge and costly: it must consider the load cycle range and test to high numbers of cycles. Additive Manufacturing (AM) for high duty components has brought to the fore the question of the effect of porosity and surface roughness on fatigue life, and how the true life of a critical component can be assessed conservatively. The authors propose the first step toward the development of a fatigue model based on well-established engineering physics principles, by creating computational specimens with modeled surface roughness and porosity, and subjected to cyclic loading using Finite Element Analysis. They show that the combination of roughness features and sub-surface pores leads to an equivalent plastic strain distribution pattern that suggests an emergent physical process that has not been reported before, and which indicates that the component strength and life reduction arising from surface roughness can be made significantly worse by the presence of porosity. The development of such phenomenological understanding should lead to improved life prediction techniques, more cost effective test procedures, and the development of better AM methods.

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In-Situ SEM Investigation of the Fatigue Behavior of Additive Manufactured Titanium Alloys

Wang

Zhao²,

Wei

et al. 2021

Lecture Notes in Civil Engineering

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Representing crack growth in additively manufactured Ti-6Al-4V

Cited by 62 publications

References 31 publications

Crack Growth in a Range of Additively Manufactured Aerospace Structural Materials

Crack Growth in a Range of Additively Manufactured Aerospace Structural Materials

Combined effect of both surface finish and sub‐surface porosity on component strength under repeated load conditions

In-Situ SEM Investigation of the Fatigue Behavior of Additive Manufactured Titanium Alloys

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