Low Cycle Fatigue and Fatigue Crack Growth Behaviors of Alloy IN718

Xie, Jizhou

doi:10.7449/1991/superalloys_1991_491_500

Cited by 5 publications

(4 citation statements)

References 1 publication

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“…Crack growth rate data available in the literature for thin foils are quite limited, and the Paris m value for similar pure Ti foils is not available. However, the m values found in the current investigation are similar to elevated m values of around 4~6 reported for other thin metallic foils that have been tested metals …”

Section: Resultssupporting

confidence: 90%

“…Holmes and co‐workers studied the mode I fatigue crack growth behaviour of 250‐µm‐thick centre‐notched Ni‐base specimens, which were subjected to tension–tension fatigue at a loading frequency of 2 Hz. It was observed that the stress intensity factor exponent m in the Paris relationship was significantly higher than commonly reported for bulk Ni‐base specimens; a similar trend was also observed in Ti‐6Al‐4V foils . It was speculated that the high‐cyclic crack growth rate in the Ni‐base foils was a result of a lower mode I lower fracture toughness.…”

Section: Introductionsupporting

confidence: 78%

“…This relationship has been shown to apply over a wide range of cyclic crack growth rates for metallic, polymeric and ceramic materials. For the limited number of foil‐thickness materials that have been studied to‐date, the m value is higher than that commonly found for bulk (thicker) samples …”

Section: Resultsmentioning

confidence: 62%

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Development of a fatigue crack growth testing apparatus and its application to thin titanium foil

Lee

Liu

Holmes

2013

Fatigue Fract Eng Mat Struct

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A B S T R A C T A low-cost experimental apparatus has been developed to investigate the mode I fatigue crack growth behaviour of thin metallic foils and sheets. The apparatus utilizes magnetic coupling between a ceramic magnet and a rotating steel disc to induce cyclic tensile loads in notched rectangular specimens. To illustrate the testing apparatus, mode I fatigue crack growth in 30-μm-thick high-purity titanium foils was studied. Experiments were performed at ambient temperature using a loading frequency of 2 Hz and a nominal stress ratio of 0.1. The cyclic crack growth data could be fit to a Paris relationship between crack growth rate and stress intensity range. The stress intensity factor exponent, m, in the Paris relationship was between 4 and 6, which is comparable with the relatively high values found in the literature for the tension-tension fatigue of other metallic bulk materials. Incomplete self-similarity analysis was used to explain the observed higher m values for thin metallic foils.Keywords fatigue crack growth rate; fatigue testing; finite element analysis; incomplete self-similarity; titanium. N O M E N C L A T U R Ea = current crack length C = the constant in the Paris relationship f = the loading frequency h = the specimen thickness J c = the fracture toughness determined by the J integral around the crack tip K c = the fracture toughness m = the exponent in the Paris relationship N = the number of fatigue cycles R = the loading ratio t = time w = the specimen width Y = the geometry correction factor z = the basic similarity parameter ΔK = stress intensity factor amplitude Δσ = the stress amplitude σ y = the yield strength I N T R O D U C T I O NFoil-thickness materials, with a thickness in the range of 10 to 250 μm, are used in a variety of applications, including micro-electro-mechanical systems (MEMS), integrated circuits, fuel cells and printers. The progressive trend of miniaturization of structural components requires knowledge regarding the mechanical behaviour and properties of thin metallic materials. As discussed in the succeeding text, the tensile, fracture and fatigue behaviour of foil-thickness materials can be very different from that observed in bulk materials. In addition to influencing the tensile properties (ductility and strength) of thin metallic foils, grain size and grain orientation can have a major effect on crack initiation, crack growth and fracture toughness. Compared with bulk materials, microstructural inclusions or precipitates in thin

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Section: Resultssupporting

confidence: 90%

Section: Introductionsupporting

confidence: 78%

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Development of a fatigue crack growth testing apparatus and its application to thin titanium foil

Lee

Liu

Holmes

2013

Fatigue Fract Eng Mat Struct

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“…Nickel-based superalloy ZSGH4169 is one of the most widely used in aero engine components, [42][43][44][45][46] especially is used for turbine disk component at 650°C. 47 In Xie, 48 the fatigue crack propagation experiment for GH4169 is carried out at 360°C, 550°C, and 650°C, corresponding to the wheel center, wheel width, and flange temperature of the turbine disk, respectively, under cyclic stress ratio R = 0:1. Aviation Industry Press 49 and He et al 50 sampling is directly from the forging, and the sampling direction is C-R.…”

Section: Validation Of the Modified Modelmentioning

confidence: 99%

Fatigue reliability analysis of crack growth life using maximum entropy method

Gan

Wang

Huang

2018

Advances in Mechanical Engineering

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In this article, a new method for fatigue reliability analysis of crack growth life based on the maximum entropy theory and a long crack propagation model is proposed. A modified generalized passivation-lancet model for long fatigue crack propagation rate is presented with explicit physical meaning. Experimental results for turbine disk alloy ZSGH4169 under different strain ratios and temperatures (at 650°C and room temperature) are used to verify the applicability of the new model. Results show that predictions by the proposed model are almost identical to the experimental data. The presented model is better than the other three models to reflect the rapid propagation characteristics of the crack. In order to perform fatigue reliability estimation, the probabilities of failure are calculated using the maximum entropy theory based on the fatigue crack growth life that derived from the proposed modified crack propagation model and the above existing three models. Results have shown that maximum entropy theory is very apt for fatigue reliability analysis of turbine disk under different loading conditions with a limited number of samples because it does not need any distribution assumptions for random variables. The effectiveness and accuracy of the combination of fatigue crack propagation models and maximum entropy method for fatigue reliability analysis are demonstrated with examples.

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Damage tolerance of wrought alloy 718 Ni- Fe-base superalloy

Chang

Koul

et al. 1994

JMEP

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Low Cycle Fatigue and Fatigue Crack Growth Behaviors of Alloy IN718

Cited by 5 publications

References 1 publication

Development of a fatigue crack growth testing apparatus and its application to thin titanium foil

Development of a fatigue crack growth testing apparatus and its application to thin titanium foil

Fatigue reliability analysis of crack growth life using maximum entropy method

Damage tolerance of wrought alloy 718 Ni- Fe-base superalloy

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