Effects of ballistic impact damage on fatigue crack initiation in Ti–6Al–4V simulated engine blades

Martinez, Christine M; Eylon, D.; Nicholas, T.; Thompson, Steven R.; Ruschau, John J.; Birkbeck, Janine C.; Porter, William

doi:10.1016/s0921-5093(01)01532-5

Cited by 44 publications

(21 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Under service loading conditions, including low-cycle fatigue (LCF), high-cycle fatigue (HCF) and combined LCF and HCF loading, damage induced by FOD can lead to premature fatigue crack initiation and propagation, ultimately causes unexpected fatigue failures in critical engine components (Ritchie et al, 1999;. Several experimental investigations (Ruschau et al, 2001(Ruschau et al, , 2003Martinez et al, 2002) have been conducted to characterise the influence of FOD for selected impact angles, on the fatigue life of Ti-6Al-4V specimens with a leading edge. From these investigations the effects of FOD on fatigue life have been quantified based on the distribution of residual stresses around the impact notch, the impact angle and the impact damage sustained by measuring the notch depth, loss of material at the notch, material shear, material folding over the leading edge and microstructural damage.…”

Section: Introductionmentioning

confidence: 99%

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

Lin

Zabeen

Tong

et al. 2015

Mechanics of Materials

View full text Add to dashboard Cite

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.

show abstract

Section: Introductionmentioning

confidence: 99%

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

Lin

Zabeen

Tong

et al. 2015

Mechanics of Materials

View full text Add to dashboard Cite

show abstract

“…Further studies [2,3,15,16] examined the effect of impact angle on fatigue strength by firing hard spheres at selected impact angles onto the specimens that are representative of the leading edge of a typical fan blade. Off-angle impacts were found to be more detrimental than head-on, and up to 50% loss in fatigue strength [2] were reported due to FOD.…”

Section: Introductionmentioning

confidence: 99%

“…Off-angle impacts were found to be more detrimental than head-on, and up to 50% loss in fatigue strength [2] were reported due to FOD. Impacts using hard cubes were carried out on plates [2], generic aerofoil specimens [15] and a more realistic aerofoil shape resembling real compressor blades [17][18][19]. The cubical projectile was considered more representative of "worst case" damage seen in service.…”

Section: Introductionmentioning

confidence: 99%

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

Spanrad

Tong

2011

Materials Science and Engineering: A

102

View full text Add to dashboard Cite

“…Projectiles in the experiments were accelerated to a velocity range . This velocity range corresponds to characteristic impact events from debris striking the underside of an aircraft during take-off and landing [7]. High-speed photography was used to record the transient deformation and damage mechanisms of beams during impact.…”

Section: Experimental Protocol For Beam Samples Under Ballistic Impactmentioning

confidence: 99%

Three-dimensional woven carbon fibre polymer composite beams and plates under ballistic impact

Turner

Liu

Zeng

et al. 2018

Composite Structures

View full text Add to dashboard Cite

Finite element (FE) simulations were conducted to understand the experimental outcomes, which showed sufficient fidelity and captured the three distinct beam response regimes. The presence of the TTT-reinforcement can suppress the inter-laminar matrix crack propagation and increase the material ballistic impact resistance for low velocity impact and high velocity impact. However, for medium velocity impact, the in-plane fibre fracture surface was found to be at the locations of TTT-reinforcement. This may suggest that the TTT-reinforcement creates weak points for the stretch-deformation dominated failure mechanism. The verified FE simulations were conducted to predict the multi-hit ballistic impact limit surfaces for the clamped circular 3D woven composite plates, and for the equivalent laminate composite without the presence of the TTT reinforcement. The numerical results suggested the presence of TTT reinforcement could improve the multi-hit ballistic resistance of the composite plates for multi-hit scenarios where the initial impact is 50%-95% of the ballistic limit of the plates.

show abstract

Effects of ballistic impact damage on fatigue crack initiation in Ti–6Al–4V simulated engine blades

Cited by 44 publications

References 5 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

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

Three-dimensional woven carbon fibre polymer composite beams and plates under ballistic impact

Contact Info

Product

Resources

About