fatiguelifebehavioroflasershockpeenedduplexstainless … · 2019. 10. 30. · tension samples of...

Research ArticleFatigue Life Behavior of Laser Shock Peened Duplex StainlessSteel with Different Samples Geometry

Cesar A Vazquez Jimenez 1 Vignaud Granados Alejo23 Carlos Rubio Gonzalez2

Gilberto Gomez Rosas4 and Sergio Llamas Zamorano1

1Facultad de Ingenierıa Mecanica y Electrica Delegacion 4 Universidad de Colima Coquimatlan Colima 28400 Mexico2Centro de Ingenierıa y Desarrollo Industrial Pie de la cuesta 702 Desarrollo San Pablo Queretaro Qro 76130 Mexico3Universidad Politecnica de Guanajuato Universidad Sur 1001 Juan Alonso Cortazar Gto 38496 Mexico4Departamento de Fısica Centro Universitario de Ciencias Exactas e Ingenierıas Universidad de GuadalajaraGuadalajara Jalisco 44430 Mexico

Correspondence should be addressed to Cesar A Vazquez Jimenez vazquez_cesarucolmx

Received 25 June 2019 Accepted 31 August 2019 Published 31 October 2019

Guest Editor Alexander Balitskii

Copyright copy 2019 Cesar A Vazquez Jimenez et al -is is an open access article distributed under the Creative CommonsAttribution License which permits unrestricted use distribution and reproduction in anymedium provided the original work isproperly cited

Two different stress raiser geometries (fillets and notched) were treated by laser shock peening (LSP) in order to analyze the effectof sample geometry on fatigue behavior of 2205 duplex stainless steel (DSS) -e LSP treatment was carried through Nd YAGpulsed laser with 1064 nm wavelength 10Hz frequency and 085 Jpulse Experimental and MEF simulation results of residualstress distribution after LSP were assessed by hole drilling method and ABAQUSEXPLICIT software respectively -e fatiguetests (tensile-tensile axial stress) were realized with stress ratio of R= 01 and 20Hz A good comparison of residual stresssimulation and experimental data was observed-e results reveal that the fatigue life is increased by LSP treatment in the notchedsamples while it decreases in the fillet samples -is is related to the residual stress distribution after LSP that is generated in eachgeometry type In addition the fatigue crack growth direction is changed according to geometry type Both the propagationdirection of fatigue crack and the anisotropy of this steel results detrimental in fillet samples decreasing the number of cycles tothe fatigue crack initiation It is demonstrated that the LSP effect on fatigue performance is influenced by the specimen geometry

1 Introduction

-rough surfaces engineering it is possible to improve thesurface properties of materials without changing the bulkmaterial Different surface treatments such as shot peeningcavitation peening laser shock peening ultrasonic peeningdeep rolling among others have proven to be effectivetechniques to increase the service time of mechanical ele-ments In recent years the LSP treatment has been focusedon fatigue behavior in different metal alloys due to its ef-fectiveness in improving their mechanical properties [1]During the first stage of the fatigue process when applyingan external load the yield stress in localized regions(crystalline defects) is exceeded -e plastic deformationcontinues accumulating as more load cycles take place untilone or more cracks are incubated By inducing residual

compression stresses through the LSP treatment and takinginto account the superposition principle in order to exceedthe yield stress in these localized regions it is necessary thatthe external load first counteract the compression stateinduced in the material and subsequently begins to deformin a tension state In this way the LSP treatment decreasesthe effect of the applied external load and delays the in-cubation time of the cracks

Several investigations have been carried out arounddifferent LSP parameters in order to optimize the LSPprocess on fatigue response of different metal alloysRubiogonzalez et al founded that as the density of pulsesincreases the fatigue crack growth rate decreases in compacttension samples of Al-6061-T6 [2] and 2205 DSS [3] -efatigue life behavior as function of laser swept direction wasoptimized for bending fatigue in Ti-6Al-2Sn-4Zr-2Mo [4]

HindawiAdvances in Materials Science and EngineeringVolume 2019 Article ID 8053248 11 pageshttpsdoiorg10115520198053248

and tensile-tensile fatigue test to 2024-T351 [5] 2205 DSS[6] and 316L [7] alloys Different fatigue behaviors wereobserved varying the swept direction for each case dem-onstrating a high influence of this LSP parameter on fatiguelife behaviors of these alloys Sheng et al [8] and Huang et al[9] analyzed the morphology of fracture surface and thefatigue crack growth rate of 6061-T6 It is founded that as thelaser pulse energy increases both the fatigue striationspacing and fatigue crack growth rate decrease -e fatigueresponse as a function of coverage area paths was analyzed

by Huang et al in Ti-6Al-4V [10] and 6061-T6 [11] alloys Itis demonstrated the fatigue properties are influenced directlyby this LSP parameter decreasing the fatigue crack growthrate in both materials

On the other hand for other test conditions such asspecimens submitted to high temperature during fatiguetest [12 13] and specimens with previous damage (pre-fatigued) [14 15] the LSP also has been an effectivetechnique to improve the fatigue properties Further theeffects on chemical composition after LSP and geometric

MoC Fe

CrNi

Mn

Mo Cr Mn Fe Ni

cpseV

wt 0021 C 122 Mn 2213 Cr 308 Mo556 Ni and Fe balance

1 63 4 52 7 80KeV

0

2

4

6

8

10

12

Figure 1 Chemical composition of 2205 cold rolled plate

100

R2

30 20

(a)

R5

30

100

(b)

Figure 2 Specimens dimensions for fatigue tests (mm) (a) fillet and (b) notched

Sample

Laser system

Optic system

Position system motorized x‐y

Lens

Mirror

Water jet

Figure 3 Experimental arrangement of LSP

2 Advances in Materials Science and Engineering

Swept directionpattern zig-zag

Zone treated by LSP

Figure 4 LSP Pulse sequence

(a) (b)

Figure 5 Finite element model of (a) notched and (b) fillet samples

50 100 150 2000Time (ns)

0

1

2

3

4

5

6

Pres

sure

(GPa

)

Figure 6 Plasma pressure profile

Table 1 Johnson-Cook parameters for DSS 2205

A (MPa) B (MPa) C n m _ε0520 84050 00124 01904 0965 1

Advances in Materials Science and Engineering 3

Untreated experimentalWith LSP simulationWith LSP experimental

150 250 35050Depth (microm)

ndash900

ndash700

ndash500

ndash300

ndash100

100

300

500

Resid

ual s

tress

(MPa

)

Figure 7 Experimental and simulation comparison of residual stress distribution

A

Aprime

Plane A-Aprime

S Max principal (Abs)(Avg 75)

ndash9978e + 08

ndash8882e + 08

ndash7786e + 08

ndash6690e + 08

ndash5594e + 08

ndash4498e + 08

ndash3402e + 08

ndash2306e + 08

ndash1210e + 08

ndash1138e + 07

+9821e + 07

+2078e + 08

+3174e + 08

(a)

B

Bprime

Plane B-Bprime


ndash7565e + 08

ndash6599e + 08

ndash5633e + 08

ndash4667e + 08

ndash3701e + 08

ndash2735e + 08

ndash1769e + 08

ndash8033e + 07

+1627e + 07

+1129e + 08

+2095e + 08

+3061e + 08

+4027e + 08

(b)

Figure 8 Results of MEF simulation (a) Residual stress distribution after LSP in notched sample and (b) Residual stress distribution afterLSP in filled sample


factors such as thickness and stress raisers also have greatinfluence on fatigue behavior Rubio-gonzalez et al [16]demonstrated that the LSP treatment in addition to theother treatment (Cold expansion) improves the fatigue lifein open-hole samples of 6061-T6 Al alloy However in-dividually the LSP treatment resulted to have a detrimentaleffect on the fatigue crack initiation stage and a beneficialeffect on the fatigue crack growth stage Spadaro et al [17]analyzed the effect of pulse density on low cycle fatigue insuper-ferritic stainless steel and it is observed that the LSPcauses thermal effects on the surface microstructuregenerating intergranular corrosion which decreases thefatigue life of this alloy Bergant et al [18] founded that theLSP increases fatigue crack growth rate in 6082-T651 Alalloy due the equilibrium tensile stresses in the center ofspecimen and notches edge as explained by Correa et al[5 7] through MEF simulation Granados-Alejo et al [19]analyzed the effect of samples thickness in 2205 DSS inwhich it is observed that in thinner samples higher fatiguelife is obtained by LSP -is behavior is explained throughthe equivalent plastic strain distribution variations asso-ciated with the change in thickness of LSP treated samplesSimilar trend about the sample thickness effects in 2024 Alalloy was observed by Achintha et al [20] For thicksamples (sim15mm) the LSP had no effect on the fatigue lifeof this alloy While for thin samples (sim5mm) the fatiguelife was improved -e operation sequence of LSP withoutcoating [21] and with coating [22] was investigated in thinopen-hole samples for 6082-T6 and LY12CZ Al alloysrespectively Similar observations are realized in bothworks and higher fatigue life was observed in samples withhole drilled after LSP than samples with hole drilled beforeLSP -is phenomenon is related to residual stress distri-bution that was assessed byMEF simulation of LSP process

It is known that other factors unrelated to LSP treatmentparameters such as sample geometry operation sequence andchemical composition among others are extremely sensitiveto fatigue behavior of different metal alloys In additions no

previous work has been reported the effect of LSP on fatiguebehavior of fillet samples In this work two different ge-ometries are compared (notches and fillets) taking into ac-count the same operation sequence and LSP conditions inorder to analyze the influence of sample geometry on fatiguelife behavior of 2205 DSS Additionally the finite elementsimulation of the LSP process on notched and fillets samplesare presented -e residual stress distribution was performedusing the commercial code ABAQUSExplicit and holedrilling method In addition the fracture surface is analyzedby SEM microscopy

2 Material and Methods

-e chemical composition results (in weight percentage) andthe spectrum obtained through the EDS analysis are shown inthe Figure 1 -e mechanical properties were investigated byconducting the tensile test according to ASTM E24-08 -eultimate tensile strength yield strength elastic modulus andelongation are 710MPa 520MPa 190GPa and 50 re-spectively Cold rolled plate of 95mm thickness was ma-chined to 4mm (samples thickness) Special care was taken tocut the samples with a high-pressure water jet to reducethermal damage on stress raiser geometries -e sample di-mensions used in this work are displayed in Figure 2 -especimens were machined with the rolling axis parallel to thelongitudinal axis As reference both 5 mm and 2mm radiuswere selected with a similar stress concentration factor(Kt = 2) for the notched and fillet samples respectively

-e laser technology system implemented to perform thetreatments is shown in Figure 3 and consists of a Nd YAGpulsed laser source with a wavelength of 1064 nm and afrequency of 10Hz During LSP the laser beam (085 J 6 ns)is directed and focused to 1mm (spot diameter) on thesample surface through an optical system -e sample ismoved with a position control device to generate the pulsesequence (zig-zag pattern) as shown in Figure 4 -e pulsesdensity and treated area were 2500 pulsescm2 and

FilletNotched

FilletNotched

ndash800

ndash600

ndash400

ndash200

0

200

Resid

ual s

tress

(MPa

)

1 2 3 40Depth (mm)

Figure 9 MEF simulation results of residual stress distribution in depth at midpoint of width


496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)

Figure 12 Fatigue crack growth evolution in notched samples (a) AR (b) LSP

Notches FilletsSample geometry

ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re

Figure 10 Fatigue life for different sample geometry in function of samples geometry for treated and untreated samples

(a) (b)

Figure 11 Fatigue crack growth direction of (a) notches (b) fillets


25times 25mm2 respectively in both sides of the samples Awater jet device was used to form thin layer water onsamples surface during the LSP treatments -e sampleswithout LSP treatment will be hereinafter called as as-re-ceived (AR)

Tensile-tensile fatigue test was carried out with MTS-810servo-hydraulic machine with a load ratio of R 01 and afrequency of 20Hz -e experiments were realized at roomtemperature in the air -e loading applied on all thespecimens was 24 kN corresponding to maximum appliedstress in reduced area of 300MPa -e fatigue crack growthwas monitored by a high-speed CCD camera using amagnification of 10x and the residual stress measurementswere realized according to ASTM E28-04 by hole drillingmethod

21 MEF Simulation -e commercial code ABAQUSEx-plicit was used to estimate the residual stress distribution-e transient response of the laser pulse and the subsequentrelaxation of the stress state constitute the numericalanalysis -e FE model is shown in Figure 5 190512 C3D8Rlinear hexahedron elements were used for fillet sample and224826 for notched sample

-e pressure pulse was applied on 25times 25mm square-e time evolution is presented in Figure 6 Peak pressure of

521GPa was obtained according to [23]-e LSP simulationprocess was simplified to one big laser shot according to [19]

-e material model used to simulate the behavior of thematerial under the shock conditions (equation (1)) was theJohnson-Cook model

σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)

with material constants are given in Table 1 [19]

3 Results and Discussion

31 Residual Stress Distribution -e comparison of theexperimental and simulation results of the residual stressesdistribution is shown in Figure 7 Compressive residualstresses are induced after LSP -e MEF simulation resultsshow a similar trend to the experimental data Figure 8shows MEF simulation of residual stress distribution in thecross-section for notched (Figure 8(a)) and fillet(Figure 8(b)) samples

It is observed that the LSP generates different residualstress distribution in each geometry type -e LSP treatmentinduces compressive residual stresses near surface Howeverthe balance of stress state generate tensile residual stresses atmiddle section of the thickness -e fillet sample present high

484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)

Figure 13 Fatigue crack growth evolution in fillet samples (a) AR (b) LSP


levels of tensile residual stresses near middle section ofthickness in comparison of the notched sample -e residualstress profile in depth at midpoint of width is shown inFigure 9 In this point the fillet sample presents a maximumvalue of tensile residual stress of 950MPa at 16mm depthWhile the notched sample presents 53MPa at 154mm deptha significant difference of 897MPa between notched and filletsamples was observed -e constant area reduction of filletsample could modify the residual stress distribution -enotched geometry has a symmetric axis in cross-direction thatdistributes the residual stress field more evenly in comparisonwith asymmetric axis corresponding to fillet sample Severalworks have demonstrated that both the pulse sequence [24 25]and the coverage area [26] modify the distribution of residualstress in sample edge and the middle of thickness Furtherother geometrical parameters such as the sample thickness alsohave a significant effect on the distribution of residual stressesas reported in [19 27] In this work the same treatmentcondition was used in both sample geometries It is evidentthat the geometry type is also an important factor whichinfluences the residual stress distribution

32 Fatigue Test Fatigue test results are shown in Figure 10It is observed that in notched samples the LSP increases thenumber of cycles to failure of 521500 for AR samples and to779450 after LSP While in fillet samples the LSP decreasesthe number of cycles to failure of 528900 for AR samplesand to 309500 after LSP It is observed that the LSP hasdifferent effects on fatigue behavior according to the samplegeometry type tested improving only the fatigue propertiesin notched samples It is correlated with residual stressresults in notched samples that showed higher compressiveresidual stress near surface and less tensile residual stress atmiddle of the sample thickness in comparison with filletsamples Figure 11 shows the fatigue crack growth directionfor each geometry type -e notched samples present asymmetric horizontal axis (perpendicular to loading axis)and the fatigue crack growth direction is given in this di-rection as shown in Figure 11(a) From Figure 11(b) it isobserved that the fillet samples present an asymmetrichorizontal axis and it has changed the fatigue short crackgrowth direction to an inclined plane and then return to thehorizontal direction perpendicular to axis loading It is

FCI

Striations

FCG

Dimples

FCG Ductile fractureFCI

AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)

Figure 14 Fracture surfaces of the specimens with filet (a d) crack initiation (b e) fatigue crack growth and (c f ) final rupture


evident that the geometry type changes the preferentialdirection of fatigue crack growth According to anisotropiceffects reported in [28 29] this direction change couldinfluence fatigue results in fillet samples

-e fatigue crack evolution in treated and untreatednotched samples is shown in Figure 12 For untreatedsamples (Figure 12(a)) the fatigue crack appears at surface at487000cycles and then 9500 cycles elapse accumulating496500 cycles to failure While in treated samples(Figure 12(b)) the fatigue crack appears at surface at 877500cycles and then 12400 cycles elapse accumulating 889900to failure It is observed that the LSP improves both thefatigue crack initiation and growth in notched samples

-e fatigue crack evolution in treated and untreatedfillet samples is shown in Figure 13 For untreated samples(Figure 13(a)) the fatigue crack appears at the surface at479000 cycles and then 5400 cycles elapse accumulating484400 cycles to failure While in treated samples(Figure 13(b)) the fatigue crack appears at surface at313000 cycles and then 6500 cycles elapse accumulating

319500 to failure It is observed that the LSP improves thefatigue crack growth stage while it is detrimental for thefatigue crack initiation stage in fillet samples It is wellknown that the fatigue crack initiation depends on mi-crostructural parameters such as crystallographic orien-tation grain size phase distribution and the interaction ofelastic and plastic properties between the austenite andferrite phases [28 30 31] In this stage the short crack ispropagating in the plane of the maximal shear stress In thefatigue crack growth stage the microstructural effects areinhibited and the fatigue crack grows perpendicular toloading axis In this stage the compressive residual stressinduced by LSP decreases stress ratio R according to su-perposition principle [32] and consequently the fatiguecrack growth rate (dadN) decreased

33 Fracture Surface -e fracture surface for notched andfillet samples is shown in Figures 14 and 15 respectively-e LSP effect changes the fatigue crack initiation zone in

(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample


Ductile fractureTransition zone

Transition zone

FCI

Striations

FCG

Figure 15 Fracture surfaces of the 4mm thick specimen (a d) crack initiation (b e) fatigue striation and (c f ) final rupture Figure 15 isreproduced from Granados-Alejo et al [19]


both samplesrsquo geometries from the border in AR samples(Figures 14(a) and 15(a)) at mid-thickness in treatedsamples (Figures 14(d) and 15(d)) -e LSP induces highlevel of compressive residual stresses and hardening layer[33] that improves the surface properties causing this shiftDetails of stable crack growth zone are shown inFigures 14(b) and 15(b) for untreated samples andFigures 14(e) and 15(e) for treated samples -e averagevalue of fatigue striation spacing in AR samples is 0748 and1337 μm for notched and fillet samples respectively Whilein treated samples the average value of fatigue striationspacing is 0346 and 0403 μm for notched and filletsamples respectively In both cases a lower value of fatiguestriation spacing after LSP was observed indicating adecrease in fatigue crack growth rate according to exper-imental results of fatigue tests-e final fracture is shown inFigures 14(c) and 15(c) for untreated samples andFigures 14(f ) and 15(f ) for treated samples In both casessimilar mechanism of ductile failure is observed

4 Conclusions

-e influence of LSP on fatigue life of 2205 DSS with dif-ferent sample geometry has been investigated -e LSPimproves the surface properties of 2205 DSS increasing thefatigue life on notched samples However the fillet samplesmodify the residual stress distribution and change the shortfatigue crack growth inhibiting the LSP effect

-e numerical simulation of residual stress distributionwas used as powerful tools to predict and correlate this resultwith the fatigue behavior of the 2205 DSS A good ap-proximation between experimental and simulation resultswas obtained

Both the reduction of fatigue striation spacing and themonitoring of fatigue crack growth corroborate that the LSPdecreases the fatigue crack growth rate in both sample ge-ometries However the propagation direction of fatiguecrack growth in fillet samples decreases the crack incubationtime -is material behavior is related to the residual stressdistribution and the anisotropy of this steel It is evident thatthe sample geometry is an important factor to the residualstress distribution and the fatigue life of 2205 DSS

Data Availability

-e experimental data used to support the findings of thisstudy are included within the article

Conflicts of Interest

-e authors declare that there are no conflicts of interestregarding the publication of this paper

Acknowledgments

-e authors thank the University of Colima CIDESIUniversity of Guadalajara and CONACYT (Mexico) fortheir support in the realization of this work

References

[1] M Kattoura S R Mannava D Qian and V K VasudevanldquoEffect of laser shock peening on residual stress micro-structure and fatigue behavior of ATI 718Plus alloyrdquo In-ternational Journal of Fatigue vol 102 pp 121ndash134 2017

[2] C Rubiogonzalez J L Ocana G Gomezrosas et al ldquoEffect oflaser shock processing on fatigue crack growth and fracturetoughness of 6061-T6 aluminum alloyrdquoMaterials Science andEngineering A vol 386 no 1-2 pp 291ndash295 2004

[3] C Rubio-Gonzalez C Felix-Martinez G Gomez-RosasJ L Ocantildea M Morales and J A Porro ldquoEffect of laser shockprocessing on fatigue crack growth of duplex stainless steelrdquoMaterials Science and Engineering A vol 528 no 3pp 914ndash919 2011

[4] S Bhamare G Ramakrishnan S R Mannava K LangerV K Vasudevan and D Qian ldquoSimulation-based optimi-zation of laser shock peening process for improved bendingfatigue life of Ti-6Al-2Sn-4Zr-2Mo alloyrdquo Surface andCoatings Technology vol 232 pp 464ndash474 2013

[5] C Correa L Ruiz De Lara M Dıaz J A Porro A Garcıa-Beltran and J L Ocantildea ldquoInfluence of pulse sequence andedge material effect on fatigue life of Al2024-T351 specimenstreated by laser shock processingrdquo International Journal ofFatigue vol 70 pp 196ndash204 2015

[6] C A Vazquez Jimenez G Gomez Rosas C Rubio GonzalezV Granados Alejo and S Herentildeu ldquoEffect of laser shockprocessing on fatigue life of 2205 duplex stainless steelnotched specimensrdquo Optics amp Laser Technology vol 97pp 308ndash315 2017

[7] C Correa L Ruiz De Lara M Dıaz A Gil-Santos J A Porroand J L Ocantildea ldquoEffect of advancing direction on fatigue lifeof 316L stainless steel specimens treated by double-sided lasershock peeningrdquo International Journal of Fatigue vol 79pp 1ndash9 2015

[8] J Sheng S Huang J Z Zhou J Z Lu S Q Xu andH F Zhang ldquoEffect of laser peening with different energies onfatigue fracture evolution of 6061-T6 aluminum alloyrdquo Opticsamp Laser Technology vol 77 pp 169ndash176 2016

[9] S Huang J Z Zhou J Sheng et al ldquoEffects of laser energy onfatigue crack growth properties of 6061-T6 aluminum alloysubjected to multiple laser peeningrdquo Engineering FractureMechanics vol 99 pp 87ndash100 2013

[10] S Huang J Sheng J Z Zhou et al ldquoOn the influence of laserpeening with different coverage areas on fatigue response andfracture behavior of Ti-6Al-4V alloyrdquo Engineering FractureMechanics vol 147 pp 72ndash82 2015

[11] S Huang J Z Zhou J Sheng et al ldquoEffects of laser peeningwith different coverage areas on fatigue crack growth prop-erties of 6061-T6 aluminum alloyrdquo International Journal ofFatigue vol 47 pp 292ndash299 2013

[12] M Kattoura S R Mannava D Qian and V K VasudevanldquoEffect of laser shock peening on elevated temperature re-sidual stress microstructure and fatigue behavior of ATI718Plus alloyrdquo International Journal of Fatigue vol 104pp 366ndash378 2017

[13] J T Wang Y K Zhang J F Chen et al ldquoEffect of laser shockpeening on the high-temperature fatigue performance of 7075aluminum alloyrdquo Materials Science and Engineering Avol 704 pp 459ndash468 2017

[14] V Granados-alejo C Rubio-gonzalez and Y Parra-torresldquoInfluence of laser peening on fatigue crack initiation ofnotched aluminum platesrdquo Structural Engineering and Me-chanics vol 6 pp 739ndash748 2017


[15] S Prabhakaran and S Kalainathan ldquoCompound technologyof manufacturing and multiple laser peening on micro-structure and fatigue life of dual-phase spring steelrdquoMaterialsScience and Engineering A vol 674 pp 634ndash645 2016

[16] C Rubio-gonzalez G Gomez-Rosas R Ruiz M Nait andA Amrouche ldquoEffect of laser shock peening and cold ex-pansion on fatigue performance of open hole samplesrdquoStructural Engineering and Mechanics vol 53 no 5pp 867ndash880 2015

[17] L Spadaro G Gomez-Rosas C Rubio-Gonzalez R BolmaroA Chavez-Chavez and S Herentildeu ldquoFatigue behavior ofsuperferritic stainless steel laser shock treated without pro-tective coatingrdquo Optics amp Laser Technology vol 93pp 208ndash215 2017

[18] Z Bergant U Trdan and J Grum ldquoEffects of laser shockprocessing on high cycle fatigue crack growth rate andfracture toughness of aluminium alloy 6082-T651rdquo In-ternational Journal of Fatigue vol 87 pp 444ndash455 2016

[19] V Granados-Alejo C Rubio-Gonzalez C A Vazquez-Jimenez J A Banderas and G Gomez-Rosas ldquoInfluence ofspecimen thickness on the fatigue behavior of notched steelplates subjected to laser shock peeningrdquo Optics amp LaserTechnology vol 101 pp 531ndash544 2018

[20] M Achintha D Nowell D Fufari E E Sackett andM R Bache ldquoFatigue behaviour of geometric features sub-jected to laser shock peening experiments and modellingrdquoInternational Journal of Fatigue vol 62 pp 171ndash179 2014

[21] G Ivetic I Meneghin E Troiani et al ldquoFatigue in laser shockpeened open-hole thin aluminium specimensrdquo MaterialsScience and Engineering A vol 534 pp 573ndash579 2012

[22] X Q Zhang L S Chen S Z Li et al ldquoInvestigation of thefatigue life of pre- and post-drilling hole in dog-bone spec-imen subjected to laser shot peeningrdquo Materials amp Designvol 88 pp 106ndash114 2015

[23] N Hfaiedh P Peyre H Song I Popa V Ji and V VignalldquoFinite element analysis of laser shock peening of 2050-T8aluminum alloyrdquo International Journal of Fatigue vol 70pp 480ndash489 2015

[24] E A Larson X Ren S Adu-Gyamfi H Zhang and Y RenldquoEffects of scanning path gradient on the residual stressdistribution and fatigue life of AA2024-T351 aluminium alloyinduced by LSPrdquo Results in Physics vol 13 Article ID 1021232019

[25] S Adu-Gyamfi X D Ren E A Larson Y Ren and Z Tongldquo-e effects of laser shock peening scanning patterns onresidual stress distribution and fatigue life of AA2024 alu-minium alloyrdquo Optics amp Laser Technology vol 108pp 177ndash185 2018

[26] K Y Luo Y F Yin C Y Wang et al ldquoEffects of laser shockpeening with different coverage layers on fatigue behaviourand fractural morphology of Fe-Cr alloy in NaCl solutionrdquoJournal of Alloys and Compounds vol 773 pp 168ndash179 2019

[27] Y Jiang X Li W Jiang et al ldquo-ickness effect in laser shockprocessing for test specimens with a small hole under smallerlaser power densityrdquo Optics amp Laser Technology vol 114pp 127ndash134 2019

[28] A Mateo L Llanes N Akdut J Stolarz and M AngladaldquoAnisotropy effects on the fatigue behaviour of rolled duplexstainless steelsrdquo International Journal of Fatigue vol 25 no 6pp 481ndash488 2003

[29] C A Vazquez Jimenez G Gomez Rosas C Rubio GonzalezV Granados Alejo and S Herentildeu ldquoEffect of laser shockprocessing on fatigue life of 2205 duplex stainless steelnotched specimensrdquo Optics amp Laser Technology vol 97 2017

[30] J C De Lacerda L C Candido and L B Godefroid ldquoEffect ofvolume fraction of phases and precipitates on the mechanicalbehavior of UNS S31803 duplex stainless steelrdquo InternationalJournal of Fatigue vol 74 pp 81ndash87 2015

[31] G Fargas N Akdut M Anglada and AMateo ldquoReduction ofanisotropy in cold-rolled duplex stainless steel sheets by usingsigma phase transformationrdquo Metallurgical and MaterialsTransactions A vol 42 no 11 pp 3472ndash3483 2011

[32] X Q Zhang H Li X L Yu et al ldquoInvestigation on effect oflaser shock processing on fatigue crack initiation and itsgrowth in aluminum alloy platerdquo Materials amp Design(1980ndash2015) vol 65 pp 425ndash431 2015

[33] C A Vazquez Jimenez R Strubbia G Gomez RosasC Rubio Gonzalez and S Herentildeu ldquoFatigue life ration-alization of laser shock peened SAF 2205 with different sweptdirectionrdquo Optics amp Laser Technology vol 111 pp 789ndash7962019


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Submit your manuscripts atwwwhindawicom

and tensile-tensile fatigue test to 2024-T351 [5] 2205 DSS[6] and 316L [7] alloys Different fatigue behaviors wereobserved varying the swept direction for each case dem-onstrating a high influence of this LSP parameter on fatiguelife behaviors of these alloys Sheng et al [8] and Huang et al[9] analyzed the morphology of fracture surface and thefatigue crack growth rate of 6061-T6 It is founded that as thelaser pulse energy increases both the fatigue striationspacing and fatigue crack growth rate decrease -e fatigueresponse as a function of coverage area paths was analyzed

by Huang et al in Ti-6Al-4V [10] and 6061-T6 [11] alloys Itis demonstrated the fatigue properties are influenced directlyby this LSP parameter decreasing the fatigue crack growthrate in both materials

On the other hand for other test conditions such asspecimens submitted to high temperature during fatiguetest [12 13] and specimens with previous damage (pre-fatigued) [14 15] the LSP also has been an effectivetechnique to improve the fatigue properties Further theeffects on chemical composition after LSP and geometric

MoC Fe

CrNi

Mn

Mo Cr Mn Fe Ni

cpseV

wt 0021 C 122 Mn 2213 Cr 308 Mo556 Ni and Fe balance

1 63 4 52 7 80KeV

0

2

4

6

8

10

12

Figure 1 Chemical composition of 2205 cold rolled plate

100

R2

30 20

(a)

R5

30

100

(b)

Figure 2 Specimens dimensions for fatigue tests (mm) (a) fillet and (b) notched

Sample

Laser system

Optic system

Position system motorized x‐y

Lens

Mirror

Water jet

Figure 3 Experimental arrangement of LSP



Zone treated by LSP


(a) (b)


50 100 150 2000Time (ns)

0

1

2

3

4

5

6

Pres

sure

(GPa

)



A (MPa) B (MPa) C n m _ε0520 84050 00124 01904 0965 1




ndash900

ndash700

ndash500

ndash300

ndash100

100

300

500

Resid

ual s

tress

(MPa

)


A

Aprime

Plane A-Aprime


ndash9978e + 08

ndash8882e + 08

ndash7786e + 08

ndash6690e + 08

ndash5594e + 08

ndash4498e + 08

ndash3402e + 08

ndash2306e + 08

ndash1210e + 08

ndash1138e + 07

+9821e + 07

+2078e + 08

+3174e + 08

(a)

B

Bprime

Plane B-Bprime


ndash7565e + 08

ndash6599e + 08

ndash5633e + 08

ndash4667e + 08

ndash3701e + 08

ndash2735e + 08

ndash1769e + 08

ndash8033e + 07

+1627e + 07

+1129e + 08

+2095e + 08

+3061e + 08

+4027e + 08

(b)









FilletNotched

FilletNotched

ndash800

ndash600

ndash400

ndash200

0

200

Resid

ual s

tress

(MPa

)

1 2 3 40Depth (mm)



496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)



ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re


(a) (b)









σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls





Zone treated by LSP


(a) (b)


50 100 150 2000Time (ns)

0

1

2

3

4

5

6

Pres

sure

(GPa

)



A (MPa) B (MPa) C n m _ε0520 84050 00124 01904 0965 1




ndash900

ndash700

ndash500

ndash300

ndash100

100

300

500

Resid

ual s

tress

(MPa

)


A

Aprime

Plane A-Aprime


ndash9978e + 08

ndash8882e + 08

ndash7786e + 08

ndash6690e + 08

ndash5594e + 08

ndash4498e + 08

ndash3402e + 08

ndash2306e + 08

ndash1210e + 08

ndash1138e + 07

+9821e + 07

+2078e + 08

+3174e + 08

(a)

B

Bprime

Plane B-Bprime


ndash7565e + 08

ndash6599e + 08

ndash5633e + 08

ndash4667e + 08

ndash3701e + 08

ndash2735e + 08

ndash1769e + 08

ndash8033e + 07

+1627e + 07

+1129e + 08

+2095e + 08

+3061e + 08

+4027e + 08

(b)









FilletNotched

FilletNotched

ndash800

ndash600

ndash400

ndash200

0

200

Resid

ual s

tress

(MPa

)

1 2 3 40Depth (mm)



496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)



ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re


(a) (b)









σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls






ndash900

ndash700

ndash500

ndash300

ndash100

100

300

500

Resid

ual s

tress

(MPa

)


A

Aprime

Plane A-Aprime


ndash9978e + 08

ndash8882e + 08

ndash7786e + 08

ndash6690e + 08

ndash5594e + 08

ndash4498e + 08

ndash3402e + 08

ndash2306e + 08

ndash1210e + 08

ndash1138e + 07

+9821e + 07

+2078e + 08

+3174e + 08

(a)

B

Bprime

Plane B-Bprime


ndash7565e + 08

ndash6599e + 08

ndash5633e + 08

ndash4667e + 08

ndash3701e + 08

ndash2735e + 08

ndash1769e + 08

ndash8033e + 07

+1627e + 07

+1129e + 08

+2095e + 08

+3061e + 08

+4027e + 08

(b)









FilletNotched

FilletNotched

ndash800

ndash600

ndash400

ndash200

0

200

Resid

ual s

tress

(MPa

)

1 2 3 40Depth (mm)



496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)



ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re


(a) (b)









σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls










FilletNotched

FilletNotched

ndash800

ndash600

ndash400

ndash200

0

200

Resid

ual s

tress

(MPa

)

1 2 3 40Depth (mm)



496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)



ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re


(a) (b)









σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls




496000 cycles

496500 cycles

495000 cycles

491000 cycles

487000 cycles

(a)

889000 cycles

889900 cycles

886000 cycles

880000 cycles

877500 cycles

(b)



ARLSP

0

200000

400000

600000

800000

1000000

Cycl

es to

failu

re


(a) (b)









σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls










σ A + Bεneq1113872 1113873 1 + Cln

_ε_ε0

1113888 11138891113890 1113891 1 minusT minus T0

Tm minus T01113888 1113889

m

1113890 1113891 (1)





484000 cycles

484400 cycles

483000 cycles

481000 cycles

479000 cycles

(a)

319000 cycles

319500 cycles

317000 cycles

315000 cycles

313000 cycles

(b)





FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls






FCI

Striations

FCG

Dimples


AR fillets sample

LSP fillets sample


(e)

Striations

FCG

(f)

Dimples

(d)

FCI

(a) (b) (c)








(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls









(a) (b) (c)

(d) (e) (f)

Striations

FCG

Micro-cracks

FCI

Dimples

Inclusions

Dimples

Inclusions

FCGFCI

AR notched sample

LSP notched sample



Transition zone

FCI

Striations

FCG




4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls





4 Conclusions




Data Availability




Acknowledgments


References






































Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls


























Advances in



Journal of

Chemistry















Journal of





Volume 2018









Journal of


Na

nom

ate

ria

ls




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