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fatigue crack growth rate

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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. 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 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 fell 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 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
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.bldgs.c9001135
EISBN: 978-1-62708-219-8
... F higher than specified by the ASTM standards. The fatigue crack growth rate through this area was much faster than expected. All of these property changes resulted from increased carbon levels, higher yield strength, and larger than normal grain size. Bridges (structural) Grain size...
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Published: 01 January 2002
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that accelerated the fatigue crack growth rate. (a) Location of cracks in the a lower wing skin pocket. (b) Machine marks More
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Published: 30 August 2021
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that had accelerated the fatigue crack growth rate. (a) Location of cracks in the lower wing skin pocket. (b) Machine marks More
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003539
EISBN: 978-1-62708-180-1
... in fatigue is macroscopically flat. This region is generally transverse to the direction of cyclic or fluctuating tensile stress that caused fatigue. However, at high loads/high fatigue crack growth rates in relatively thin components made of relatively tough material, a transition to propagation on a slant...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006776
EISBN: 978-1-62708-295-2
... and/or bending loads. This region is generally transverse to the direction of cyclic or fluctuating tensile stress that caused fatigue. However, at high loads/high fatigue crack growth rates in relatively thin components made of relatively tough material, a transition to propagation on a slant plane can occur...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001144
EISBN: 978-1-62708-217-4
... is useful for analysing crack growth rates, the presence of random loading makes the process much more difficult ( 1 , 2 , 3 ). Fig. 3 Fatigue striations from random loading on fracture surface of failed spar. (638× approx.). The fatigue crack progressed approximately 5.6 mm in a uniform mode...
Book Chapter

Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003544
EISBN: 978-1-62708-180-1
... these topics in more detail. Fatigue Crack Growth Rates The limitation of the S - N and ε- N methods is the inability of the controlling quantities to make sense of the presence of a crack. In traditional stress analysis of applied loads, basic elasticity calculations show that both stress and strain...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001081
EISBN: 978-1-62708-214-3
... are presented in Fig. 15 . The spin-pit tests showed that the crack propagation rates remained relatively constant up to a crack length of approximately 10 mm (0.4 in.). A typical fatigue striation pattern observed during spin-pit crack growth is shown in Fig. 16 . Using striation counting methods...
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
... initiation had taken 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...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001291
EISBN: 978-1-62708-215-0
... was characteristic of hydrogen embrittlement cracking, which probably would have occurred before the strut was baked (de-embrittlement) to remove residual hydrogen. Although it was not possible to establish the fatigue crack growth rate from observations of the crack surfaces, the very sharp crack tip associated...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006781
EISBN: 978-1-62708-295-2
... and Begley ( Ref 11 , 12 ), who used it to correlate the fatigue crack growth behavior of specimens of different geometries under elastic-plastic and fully plastic conditions. They proposed a relationship between the fatigue crack growth rate per cycle, da / dN , and Δ J : (Eq 29) da dN = C...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c9001136
EISBN: 978-1-62708-229-7
... corresponding to particular fatigue crack growth rates (da/dN). This follows since, in the linear region of the fatigue crack propagation curve at least, each striation corresponds to one fatigue cycle. Fig. 5 Low magnification fractograph of the origin of failure (area D of Fig. 3(b) ). Fatigue...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003546
EISBN: 978-1-62708-180-1
... growth rate per cycle, da / dN , and Δ J : (Eq 14) d a / d N = C ( Δ J ) q where C and q are material parameters that are obtained from regression of the fatigue crack growth data. Also, under elastic conditions, the following relationship holds ( Ref 16 , 17 , 18 ): (Eq...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006774
EISBN: 978-1-62708-295-2
... provides clues as to whether the material is high strength (smoother) or low strength (rougher) and whether fracture occurred as a result of cyclic loading. The surfaces from fatigue crack growth are typically smoother than monotonic overload fracture areas. The monotonic overload fracture of a high...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.rail.c9001531
EISBN: 978-1-62708-231-0
... (yield strength, σ 0.2 , and tensile strength) decreases as the carbon content decreases. However, the fatigue crack growth rates in the Paris regime and fatigue thresholds (Δ K th ) were found to be insensitive to composition and microstructure. It is noticeable that despite the variation in carbon...