Fatigue crack growth from foreign object damage under combined low and high cycle loading. Part II: A two-parameter predictive approach

Ding, Jian; Hall, Richard F.; Byrne, J.; Tong, Jie

doi:10.1016/j.ijfatigue.2006.10.014

Cited by 26 publications

(24 citation statements)

References 17 publications

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Section: Discussionmentioning

confidence: 82%

“…11. This may be an important reason why crack growth rates from FOD are higher than those obtained from long crack growth data under the corresponding applied stress ratios, as observed from experimental work [9,10].For future study, one important issue is to experimentally measure the residual stress relaxation after FOD to validate the present model. Boyce et al [3] has reported both experimental and numerical results on the relaxation of residual stresses induced by a static indentation.…”

mentioning

confidence: 86%

“…Experimental observations in [10,11] have clearly shown a mode I crack propagation behaviour from FOD, for which the crack grows along the plane normal to the x-direction (fatigue load direction). Therefore, in this work only the stress field and its relaxation in the xdirection are considered.…”

Section: Stress Relaxation Under Cyclic Loadingmentioning

confidence: 99%

“…In addition, the study also suggested a two-parameter crack growth model to correlate fatigue crack growth data from FOD, in which the effects of stress concentration and residual stress incurred by FOD was incorporated by the El Haddad small-crack theory [19]. However, the relaxation of residual stresses under cyclic fatigue loading was not considered in [10]. In the present study this issue is addressed by a hybrid explicit-implicit finite element approach, which allows the transition from a rate dependent material model (for dynamic impact modelling) to a cyclic hardening material model (for static stress analysis).…”

mentioning

confidence: 99%

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Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Davis

Ding²,

Sun

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part L:

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In this study, the phenomenon of residual stress relaxation from foreign object damage (FOD) is numerically simulated using a hybrid explicit-implicit finite element method. The effects of both low-cycle and high-cycle fatigue loadings on stress relaxation were studied. FOD is first simulated by firing a 3mm cube impacting onto a plate of Ti-6Al-4V at 200m/s. The FOD impact produces two distinct stress concentrations: one is compressive directly beneath the impact site, the other is tensile around the outer edge of the impact. The plate was then assumed to be subjected to a cyclic fatigue loading. The stress relaxation was investigated under a range of stress ratios and maximum applied stresses. Two different material models were considered for the simulations, namely an elastic-perfectly plastic model and a non-linear kinematic hardening model. Keywords: finite element; impact; foreign object damage (FOD); residual stress; stress relaxation. normal stress component in x-direction, i.e. in the direction of applied load σ ys yield stress 2 σ ys (  ) strain rate sensitive yield stress σ y stress component in y-direction σ z stress component in z-direction 1. Introduction Dynamic impact and subsequent fatigue under cyclic loading conditions demonstrate a very demanding failure mode, which occurs in a number of mechanical applications. Impact leads to either beneficial or detrimental effects on the fatigue performance. For example, the cold working process of shot-peening is used to create a beneficial compressive residual stress field over the surface of the component. This compressive residual stress inhibits surface crack growth and thereby leads to an increase in fatigue life. Spherical shots made from hardened materials are typically used for the shot peening, fired at velocities in the range of 40-100 m/s. [1]. The detrimental effects of impacts are observed in such a phenomenon as Foreign Object Damage (FOD), which occurs primarily during the takeoff and landing periods of aircraft flights, where millimetre sized debris in the form of hard particles such as sand and grit are ingested into aero engines [2][3][4]. These particles impact the fan and early stage compressor blades, typically made from the titanium alloy Ti-6Al-4V, at speeds in the range of 200 to 350 m/s. Impacts on the leading edge of the blades cause the most severe damage, which is in the form of notch like craters and gives rise to stress concentrations, residual stresses, microcracks around the impact site and distortion of the materials microstructure [3]. The combination of the fatigue loading and the residual stress field induced by the impact can make the impact region a preferential site for both fatigue crack initiation and growth. This reduces the fatigue resistance of the blades and in some cases causes them to fail prematurely. It has been reported that the cost of FOD to both the civil and military aircraft industries is greater than $4 billion annually [4]. NotationTo gain insight into the interaction between FOD and fati...

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Section: Discussionmentioning

confidence: 82%

mentioning

confidence: 86%

Section: Stress Relaxation Under Cyclic Loadingmentioning

confidence: 99%

mentioning

confidence: 99%

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Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Davis

Ding²,

Sun

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part L:

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“…anomaly geometry and the residual stress level [7]. The stress concentration factor peaks near the anomaly while the residual stresses have very little influence.…”

Section: Modelling Of Fatigue Crack Propagation From Surface Anomaliesmentioning

confidence: 94%

Fatigue crack growth from handling surface anomalies in a nickel based superalloy at high temperature

Gourdin

Doremus

Nadot

et al. 2014

MATEC Web of Conferences

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Abstract. Aircraft engine manufacturers have to demonstrate that handling surface anomalies in sensitive areas of discs are not critical for in-service life of a component. Currently, the models used consider anomalies as long cracks propagating from the first cycle, which introduces a certain degree of conservatism when calculating the fatigue life of surface flaws. Preliminary studies have shown that the first stages of crack propagation from surface anomalies are responsible for the conservative results. Thus, the aim of the study is to characterize the crack propagation from typical surface anomalies and to establish a new crack growth model, which can account for the micro-propagation stage. To separate the effects of the geometry of the anomalies and the residual stress state after introduction of the surface flaws, two V-type anomalies are studied: scratches and dents. Different studies have shown that the residual stresses beneath the anomalies seem to control the fatigue life of samples exhibiting scratches and dents. In order to monitor the crack micro-propagation, a direct current potential drop technique, coupled with heat tints is used during fatigue tests at elevated temperature. Thermal treatments releasing the residual stresses are also used to decouple the effect of crack morphology and residual stresses.

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Evolution of a laser shock peened residual stress field locally with foreign object damage and subsequent fatigue crack growth

2015

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Evolution of a laser shock peened residual stress field locally with foreign object damage and subsequent fatigue crack growth. Acta Materialia, http://dx.doi.org/10.1016/j.actamat.2014.09.032 conditions. The ballistic FOD impacts were introduced by impacting a cube edge at an angle of head-on (0 degrees) to the leading edge. The residual stress distributions have been mapped by synchrotron X-ray diffraction prior to cracking and subsequent to short (~1 mm) and long (up to 6 mm) crack growth. 2The results suggest that the local residual stress field is highly stable even to the growth of relatively long cracks.

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Fatigue crack growth from foreign object damage under combined low and high cycle loading. Part II: A two-parameter predictive approach

Cited by 26 publications

References 17 publications

Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Fatigue crack growth from handling surface anomalies in a nickel based superalloy at high temperature

Evolution of a laser shock peened residual stress field locally with foreign object damage and subsequent fatigue crack growth

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