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crack-growth rates

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Published: 01 January 2002
Fig. 39 (a) Comparison of creep-fatigue crack growth rates with fatigue crack growth plotted as a function of Δ K . (b) The effect of hold time estimated for engineering structures when the creep crack growth rate is plotted as a function of ( C t ) avg More
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Published: 01 June 2019
Fig. 8 Fatigue crack growth rates through the segregated region compared to known growth rate values. More
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Published: 15 May 2022
Fig. 18 Crack-growth rate ( da / dN ) as a function of the energy-release rate, J I , for a single-edge notched polycarbonate specimen with 0.33 mm (0.013 in.) thickness More
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Published: 15 May 2022
Fig. 19 Crack-growth rate ( da / dN ) as a function of the energy-release rate, J I (tearing energy), for a rubber compound. J Ic , critical energy-release rate More
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Published: 01 January 2002
Fig. 11 The measured crack growth rate (crack length versus time) determined by optical measurements or fractographic evaluation used to validate life prediction estimates. In this example, for an aircraft wing, the predicted crack growth and the actual crack growth based on measured crack More
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Published: 30 August 2021
Fig. 11 The measured crack growth rate (crack length versus time) is determined by optical measurements or fractographic evaluation in order to validate life-prediction estimates. In this example for an aircraft wing, the predicted crack growth and the actual crack growth (which is based More
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Published: 01 January 2002
Fig. 6 Schematic illustration of variation of fatigue-crack-growth rate, da / dN , with alternating stress intensity, Δ K , in steels, showing regions of primary crack-growth mechanisms. Source: Ref 5 More
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Published: 01 January 2002
Fig. 7 Pearson plot of crack-growth rate as a function of K for short surface cracks and through-cracks. Source: Ref 6 More
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Published: 01 January 2002
Fig. 13 Effect of hold time on the fatigue crack growth rate properties of 2.25Cr-1Mo cast steel. The 2 h hold time tests were performed in steam at 538 °C (100 °F). Source: Ref 13 More
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Published: 01 January 2002
Fig. 19 Graph showing the influence of load on the LME crack-growth rate for the experimental conditions described in text. Copper-free tensile strength at 1100 °C (2010 °F), % More
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Published: 01 January 2002
Fig. 13 Crack growth rate data for 2024-T3 aluminum at R = 0 ( example 2 ). Source: Ref 33 More
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Published: 01 January 2002
Fig. 3 Variation of the fatigue crack growth rate as a function of temperature. (a) Temperature effect on fatigue crack threshold and growth rates. (b) Variation of fatigue crack growth rates at Δ K of 30 MPa m (27 ksi in. ) More
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Published: 01 June 2019
Fig. 13 Comparison between the crack growth rate from the fracture surface (hatched) and the literature results for this material More
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Published: 15 January 2021
Fig. 12 Schematic illustration of variation of fatigue crack-growth rate, da / dN , with alternating stress intensity, Δ K , in steels, showing regions of primary crack-growth mechanisms. Source: Ref 13 More
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Published: 15 January 2021
Fig. 13 Pearson plot of crack-growth rate as a function of K for short surface cracks and through-cracks. Source: Ref 16 More
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Published: 15 January 2021
Fig. 17 Effect of hold time on the fatigue crack growth rate properties of 2.25Cr-1Mo cast steel. The 2 h hold time tests were performed in steam at 538 °C (1000 °F). Source: Ref 28 More
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Published: 01 December 1992
Fig. 12 Cyclic crack growth rate as a function of the change in stress intensity for 6061-T651 aluminum alloy. Source: Ref 1 . More
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Published: 01 December 1992
Fig. 18 Log-log da/dN versus delta K fatigue crack growth-rate test results for 310 MPa (45 ksi) maximum stress and stress ratio of 0.73. The scatterband (two parallel lines) is for quenched and tempered martensitic steels from NCHRP 12–14. Note that the A517 grade, F, plate D, test results More
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001021
EISBN: 978-1-62708-214-3
... in service, the Royal Australian Air Force requested that the crack growth rate during service be determined. The loading history of the aircraft was made available in the form of flight by-flight records of the counts from the vertical accelerometer sensors fitted to the airframe and a series of “overstress...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.marine.c9001657
EISBN: 978-1-62708-227-3
... place in the blade trailing edge. An estimate of the crack-growth rate for the stage II fatigue fracture region coupled with the metallographic results helped to identify the final mode of the turbine blade failure. A detailed metallographic and fractographic examination of the air-cooled vane revealed...