Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Spanrad, Sven; Tong, Jie

doi:10.1016/j.msea.2010.11.045

Cited by 102 publications

(45 citation statements)

References 28 publications

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“…9a); for the 45°impact, a notch with a significantly varying depth at the entrance and the exit of the projectile was predicted, although due to the removal of damaged elements during the FE simulation (Fig. 9b), no material pile-up was found in the notch root, consistent with the experimental observations by Spanrad and Tong (2011). The notch depths predicted by the simulations are 1.29 and 0.77 mm for head-on and 45°impacts respectively, which compare favourably with the measured values of 1.43 and 0.78 mm.…”

Section: Comparison Of Residual Stresses From Fe Simulation and Synchsupporting

confidence: 82%

“…Our experimental studies of FOD on laser-shock peened Ti-6Al-4V aerofoils (Spanrad and Tong, 2011) have shown that, for head-on impacts, a ''V'' notch was obtained on the leading edge with typical features of material folding and piling up. By contrast, for 45°impacts, the projectile ''sheared off'' part of the leading edge during impact, so loss of material is an important feature of 45°impacts.…”

Section: Materials Model and Parameter Determinationmentioning

confidence: 89%

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Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

Lin

Zabeen

Tong

et al. 2015

Mechanics of Materials

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a b s t r a c tForeign object damage (FOD) to the leading edge of aerofoils has been identified as one of the main life-limiting factors for aeroengine compressor blades. Laser-shock peening (LSP) has been proposed as a means of increasing the material's resistance to such impact damage. In this work, a three-dimensional finite element (FE) model has been developed to simulate the residual stresses due to head on (0°) and 45°impacts by a cuboidal projectile on aerofoil specimens treated with LSP. The Johnson-Cook (JC) material model was employed to describe the strain rate-dependent material behaviour; whilst the JohnsonCook dynamic failure model was considered in 45°FOD simulation, where significant loss of material occurred. The strain rate sensitivity of the model at selected high strain rates was assessed against the data from the literature. The numerical results from the simulation of head-on impact were compared with the measurements by depth-resolved synchrotron X-ray diffraction on the mid-plane. The models were then used to predict the 3D residual stress distributions due to 0°and 45°FOD impacts, and the results were compared with the strain maps obtained from high-energy synchrotron X-ray diffraction. Good to excellent correlations between the simulations and the measurements have been found.

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Section: Comparison Of Residual Stresses From Fe Simulation and Synchsupporting

confidence: 82%

Section: Materials Model and Parameter Determinationmentioning

confidence: 89%

Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

Lin

Zabeen

Tong

et al. 2015

Mechanics of Materials

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“…The specimens were fatigued by Spanrad and Tong at Portsmouth University as described in [32] under 4-point bend and constant amplitude cyclic loading using a servohydraulic twin actuator 100kN testing machine. The support span was 107 mm and the loading span was 57 mm.…”

Section: B Specimen Studiedmentioning

confidence: 99%

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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“…This allows less thermal relaxation of residual stresses after LSP when subjected to high temperatures [2]. On the fatigue performance of Ti-6Al-4V, crack initiation and early crack growth on aerofoil specimens due to foreign object damage (FOD) and subsequent fatigue crack growth were examined after applying LSP [3]. It was reported that LSP has improved the crack growth resistance post FOD.…”

Section: Introductionmentioning

confidence: 99%

Investigation of laser shock peening effects on residual stress state and fatigue performance of titanium alloys

Maawad

Sano

Wagner

et al. 2012

Materials Science and Engineering: A

192

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Laser shock peening can potentially enhance fatigue life of titanium components by inducing compressive residual stresses in surface layers much deeper than caused by traditional shot peening (SP). In the present study, the high cycle fatigue (HCF) performance of α Ti-alloy Ti-2.5Cu, (α + β) Ti-alloy TIMETAL 54M and the metastable β Ti-alloy TIMETAL LCB was investigated after laser shock peening without coating (LPwC). The fatigue results were interpreted by examining the changes of surface morphology, microhardness and residual stress generated in the surface layer. Furthermore, thermal stability of residual stresses in aged Ti-2.5Cu, as an example, was evaluated after annealing LPwC-treated material at various elevated temperatures and exposure times by applying a Zener-Wert-Avrami-approach. The depth profiles of residual stresses were obtained by means of synchrotron X-ray diffraction or by incremental hole drilling method. Results revealed that the HCF performance of Ti-2.5Cu and TIMETAL LCB was markedly improved after LPwC, while it was deteriorated in TIMETAL 54M. Compared to LPwC, better 10 7 fatigue strength of Ti-2.5Cu was obtained after ball-burnishing (BB). Moreover, LPwC-induced residual stresses are thermally more stable than shot peening-induced ones.

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Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Cited by 102 publications

References 28 publications

Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

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

Investigation of laser shock peening effects on residual stress state and fatigue performance of titanium alloys

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