Extensive Study of Low Fatigue Crack Growth Rates in A533 and A508 Steels

Paris, Paul C.; Bucci, R. J.; Wessel, E.T.; Clark, W. G.; Mager, T.R.

doi:10.1520/stp34119s

Cited by 197 publications

(31 citation statements)

References 8 publications

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“…The K th of the T6 sample is the lowest, with the value about 2.5 MPa m 1/2 , whereas the T5 sample has the highest K th value about 5.5 MPa m 1/2 . At the stage 2 of the FCP, the curves can meet the Paris criterion [21]. However, the FCP rate of the T6 sample is slightly higher than those of the forged and T5 samples.…”

Section: Resultsmentioning

confidence: 93%

The fatigue crack propagation behavior of the forged Mg–Zn–Y–Zr alloy

Liu

et al. 2007

Journal of Alloys and Compounds

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Section: Resultsmentioning

confidence: 93%

The fatigue crack propagation behavior of the forged Mg–Zn–Y–Zr alloy

Liu

et al. 2007

Journal of Alloys and Compounds

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“…In the United States, the threshold regime is experimentally defined by using a load-reduction test procedure [1]. In the early 1970's, a load-reduction test method was developed by Paris et al [2,3] to generate data at low stress-intensity-factor ranges and approaching threshold conditions. Later, Hudak et al [4] finalized the method, which was incorporated into ASTM E-647 fatigue-crack-growth-rate testing standard.…”

Section: Introductionmentioning

confidence: 99%

Compression precracking methods to generate near-threshold fatigue-crack-growth-rate data

Newman

Yamada

2010

International Journal of Fatigue

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Abstract. Some of the fatigue-crack-growth-rate data generated in the threshold and near-threshold regimes on two aluminum alloys (7075-T651, 7075-T7351), a titanium alloy (Ti-6Al-4V E-STOA), a high-strength 4340 steel and a nickel-based superalloy (Inconel-718) were determined by using the compression precracking constant-amplitude (CPCA) and compression precracking loadreduction (CPLR) test methods. Tests were conducted over a range in stress ratios (R = 0.1, 0.4 and 0.7) on compact specimens. Results are compared with threshold and near-threshold data generated on the same materials using the ASTM E-647 load-reduction test procedures. One of the aluminum alloys (T651) and the 4340 steel showed very little difference between the methods; however, the other materials showed significant differences with the compression precracking test methods giving lower thresholds and faster crack-growth rates than the ASTM load-reduction method.

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“…Results have been published suggesting that the R-ratio dependence may itself be thickness dependent [55] but other work has failed to confirm this [56].…”

Section: Thresholdsmentioning

confidence: 99%

A Review of Fatigue Crack Growth Characterisation by Linear Elastic Fracture Mechanics (Lefm). Part I—principles and Methods of Data Generation

Allen

Booth

Jutla

1988

Fatigue Fract Eng Mat Struct

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Ahstmet-The application of linear elastic fracture mechanics (LEFM) to the characterisation of fatigue crack growth has been reviewed. In Part I the present understanding of the factors influencing growth rate is summarised, and the current methods of fatigue crack growth rate data generation are considered in the light of this. In Part 11, documents are reviewed which provide advice on the prediction of fatigue crack growth and also those national standards in which fatigue crack growth considerations are implicit. NOMENCLATUREBecause of the nature of this review it is not possible to provide a precise nomenclature. Where possible, terminology consistent with the source document has been adopted. The following general terms occur most frequently: A, C, C,, =constants in the Paris equation u = crack length B = specimen thickness d = grain diameter du/dN = fatigue crack growth rate per cycle dq5/dA = rate of change in compliance with crack area E = Young's modulus E' = E for plane stress or E/(1 -v 2 ) for plane strain G = crack extension force per unit thickness J = Jcontour integral K = stress intensity factor Kal = parameters relating to the dependence of threshold on prior load history K.fb Kl K, = non-plane strain fracture toughness K,c = plane strain fracture toughness K = mean stress intensity factor N = number of loading cycles P = applied load K , , = maximum value of K during a loading cycle tn, n = exponents in the Paris equation PmX = maximum load during a cycle P,j, = minimum load during a cycle R = stress or load ratio (Pmn/Pmm) W = specimen width (or half width of a BSI CCT specimen) Y = stress intensity factor function Au = change in crack length AK = stress intensity factor range (K,,,,, -Lin) 'Author to whom correspondence should be addressed. U = AK,,/AK 45 F.F.E.M.S. I lil-D 46 R. J. ALLEN et al. AKeR= the range of K over which a crack is fully open on loading AKth = fatigue crack growth threshold A& = initial value of AK at the start of a test AP = load range (P,,, -P,,,) S = crack tip opening displacement (CTOD) v = poisson's ratio of = flow stress [ = (uTs + uys)/2] uTs = tensile strength uys = yield or 0.2% proof strength ux = stress in the x direction (see Fig. 1) uy = stress in the y direction (see Fig. 1) Units = MPa, m unless otherwise stated.

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Extensive Study of Low Fatigue Crack Growth Rates in A533 and A508 Steels

Cited by 197 publications

References 8 publications

The fatigue crack propagation behavior of the forged Mg–Zn–Y–Zr alloy

The fatigue crack propagation behavior of the forged Mg–Zn–Y–Zr alloy

Compression precracking methods to generate near-threshold fatigue-crack-growth-rate data

A Review of Fatigue Crack Growth Characterisation by Linear Elastic Fracture Mechanics (Lefm). Part I—principles and Methods of Data Generation

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