Short Fatigue Crack Propagation Thresholds of Railway LZ50 Axle Steel
超高韧性水泥基复合材料疲劳裂缝扩展公式的理论与试验研究

第30卷第11期V ol.30 No.11 工程力学2013年11 月Nov. 2013 ENGINEERING MECHANICS 67 文章编号:1000-4750(2013)11-0067-08超高韧性水泥基复合材料疲劳裂缝扩展公式的理论与试验研究刘问1,3,徐世烺2,李庆华2(1. 北京林业大学水土保持与荒漠化防治教育部重点实验室,北京100083;2. 浙江大学高性能建筑结构与材料研究所,杭州310058;3. 大连理工大学结构研究所,大连116024)摘要:该文基于Paris公式,对具有应变硬化和多缝开裂特征的超高韧性水泥基复合材料(UHTCC)的疲劳裂缝扩展理论进行了理论研究,并通过试验进行验证。
研究表明,Paris公式适用于UHTCC。
其中:裂缝扩展参数由裂缝面积扩展A表示;与之相应,使用复合断裂能增长量ΔJ代替应力强度因子变化量ΔK。
基于试验,该文求出UHTCC的疲劳裂缝扩展门槛值,即当疲劳过程中的断裂能幅值ΔJ小于某一临界值ΔJ th时,疲劳裂缝不扩展。
在疲劳过程中,UHTCC的裂缝覆盖面积随疲劳过程呈三阶段线性发展,与疲劳变形的发展趋势一致。
UHTCC的疲劳裂缝扩展随疲劳最大荷载与荷载幅值的增大而加速发展。
关键词:结构工程;疲劳裂缝扩展;Paris公式;超高韧性水泥基复合材料;裂缝扩展门槛值中图分类号:TU317.1; TU502+.6 文献标志码:A doi: 10.6052/j.issn.1000-4750.2012.05.0362THEORICAL AND EXPERIMENTAL STUDY ON FATIGUE CRACK PROPAGATION LAW OF ULTRA-HIGH TOUGHNESS CEMENTITIOUSCOMPOSITELIU Wen1,3 , XU Shi-lang2 , LI Qing-hua2(1, Key Laboratory of Soil & Water Conservation and Desertification Combating, Ministry of Education, Beijing Forestry University, Beijing, 100083, China;2, Institute of Advanced Engineering Structures and Materials, Zhejiang University, Hangzhou, 310058, China;3, Institute of Structural Engineering, Dalian University of Technology, Dalian, 116024, China)Abstract:Based on Paris law of fatigue crack propagation rate, a theoretical and experimental investigation was taken to study the fatigue crack propagation mechanism of ultra-high toughness cementitious composite, which exists the characteristics of strain hardening and multiple cracking. Paris law is applicable for this material, with the two parameters redefined: the covering area of multiple cracks, A, and the composite fracture energy, J. A fatigue crack propagation threshold is found in the experiment. During the whole fatigue progress, there exist three linear stages for the development of crack covering area, in correspondence with the three stages of fatigue deformation. Moreover, the crack propagation rate speeds up with the increases of the maximum fatigue load and the fatigue load range.Key words:structural engineering; fatigue crack propagation; Paris law; ultra-high toughness cementitious composite; crack propagation threshold———————————————收稿日期:2012-05-19;修改日期:2012-09-25基金项目:国家自然科学基金项目(51308046)通讯作者:刘问(1983―),女,山东人,讲师,博士,从事高性能复合材料的损伤与断裂等方面的研究(E-mail: liuwen@).作者简介:徐世烺(1953―),男,湖北人,教授,博士,院长,从事混凝土及纤维混凝土断裂、新型材料与结构等方面的研究(E-mail: slxu@);混凝土类建筑材料的疲劳寿命是由3个阶段组成的:疲劳裂纹形成、疲劳裂缝扩展与断裂[1]。
crack propagation

Vol.63 No.1, 35-42, 2007. 1
には幹線道路の立体交差を短期間に実現するために,鋼 床版構造が全国的に数多く採用された.しかしながら, 架設後数年でデッキ貫通型・ノド貫通型の疲労き裂がト ラックのタイヤが通過する位置の周辺に多数発見された 例が報告されている 3).また,1966 年に当時の技術の粋 を集めて架設されたイギリスのセバーン橋においても, わずか 15 年後に疲労損傷の報告がなされている 4).オラ ンダでも,Van Brienenoord 可動橋を始めとして 2004 年ま でに,交通量の多い 10 橋からデッキ貫通型疲労き裂が 発見されたと報告されている 5). 三木ら 6)は大型疲労試験および解析から,トラフリ ブ・横リブ交差部におけるトラフリブとデッキプレート の溶接について,溶け込み深さが疲労強度に対して非常 に重要であることを示している.また,森 7)はこのき裂 に対し,トラフリブの一部を模した試験体を用いた実験 と解析から,デッキプレートとトラフリブの溶接の溶け 込み深さについて論じている.筆者ら 2)は詳細な FEM 解 析結果と実橋での車両走行試験の結果を比較検討するこ とで,床版の局部曲げが原因であると結論付けた.ま た,疲労き裂を抑制する一つの方法としてデッキの変形 を抑制するためにデッキ厚を増すことを提案している. しかしながら,ルートき裂がデッキ板厚貫通方向に伸び る発生要因については,明らかになっていない. 本研究ではデッキの変形挙動に着目して,デッキとト ラフの溶接部に生じるき裂を抑制する構造について検討 を行う.
半径0.5~1.0mm 程度
図-2 エフェクティブノッチストレス算出モデル
s
s
s t
デッキプレート
Fatigue Crack Growth Analysis of Fiber

number of microscopic changes during fatigue loading, fatigue crack growth can be considered the damage most responsible for fatigue life of FRCs and, therefore, must be focused on. FRCs fail in fatigue when a fracture propagates unstably subsequent to stable crack growth under fatigue loading.4*5 Thus, fatigue life of FRCs is controlled by fatigue crack growth behavior. Fatigue crack growth in FRCs is affected by three main factors: matrix fatigue crack growth law specific to a matrix, crack bridging by fibers, and fatigue damage in the fiber-matrix interface and/or bridging fibers. These three factors are discussed in the following sections. First, matrix fatigue crack growth is quantified with the Paris law, which relates the crack growth rate to the intensity factor amplitude. crack-tip-stress Second, a cyclic constitutive law between the crack bridging stress amplitude and the crack opening displacement amplitude due to fibers and aggregates is described. With the cyclic constitutive law, the crack-tip-stress intensity factor amplitude, which is reduced by crack bridging, can be evaluated. Finally, the interfacial frictional bond degradation under cyclic sliding is quantified assuming that the bond degradation is governed by the accumulated crack opening displacement change. Fatigue damage on matrix: fatigue crack growth Fatigue crack growth has been observed to obey a Paris law type equation for metals, ceramics, and concrete.6-‘9 The Paris law gives the relation between the crack growth rate and the intensity factor amplitude, crack-tip-stress namely
Fatigue life and fatigue crack propagation behavior of JLF-1 steel

Fatigue life and fatigue crack propagation beha v ior of JLF-1steelH.K.Yoon a,1,S.P.Lee a ,B.H.Min a ,S.W.Kim b ,Y.Katoh c ,A.Kohyama ca Department of Mechanical Engineering,Dong-Eui Uni v ersity,24,Gaya-Dong,Busan Jin-Gu,Busan 614-714,Republic of Korea bDepartment of Mechanical Engineering,Graduate School,Dong-Eui Uni v ersity,24,Gaya-Dong,Busan Jin-Gu,Busan 614-714,Republic of KoreacInstitute of Ad v anced Energy,Kyoto Uni v ersity,Gokasho,Uji,Kyoto 611-0011,JapanAbstractThe objecti v e of this study is to in v estigate fatigue life and fatigue crack propagation beha v ior in the reduced acti v ation ferritic steel JLF-1.The experiment of fatigue life for JLF-1steel ha v e been carried out for the stress ratio R 00at room temperature and 4008C.The fatigue crack propagation beha v ior of the JLF-1steel was in v estigated by the constant amplitude loading test for the stress ratios R 00.1,0.3and 0.5,respecti v ely.The effects of stress ratios and specimen size on the fatigue crack growth beha v iors for JLF-1steel were discussed within the Paris law.The fatigue life test performed under the room temperature and 4008C.At room temperature,the fatigue limits of longitudinal and trans v erse direction to the rolling direction were 480and 490MPa at 1)107cycles,respecti v ely.Also,at 4008C,the fatigue limits of longitudinal and trans v erse direction to the rolling direction were 400,416MPa at 1)107cycles,respecti v ely.The base material of JLF-1steel showed the isotropic beha v ior in fatigue properties of the rolling direction and the test temperature.The fatigue crack propagation rate of a half size specimen was similar to that of a full size specimen at the stress ratios of 0.1,0.3and 0.5,respecti v ely.The fatigue crack propagation beha v ior of this material can be e v aluated by using half size specimens.#2002Else v ier Science B.V.All rights reserved.Keywords:Reduced acti v ation ferritic steel;High cycle fatigue life;Fatigue limit stress;Fatigue crack propagation rate (d a /d N );Stress intensity factor range (D K );Effect of stress ratios;Effect of rolling direction;Full and half size specimen1.IntroductionAs a kind of reduced acti v ation ferritic steels (RAFs),the JLF-1(9Cr Á2W ÁV ÁTa)steel has been de v eloped and in v estigated by the acti v e cooperation with Japanese Uni v ersities under theIEA test program [1Á4].The RAFs mounted in a high magnetic field such as fusion reactor compo-nents may be affected by the operating cycle and the mechanical v ibration that is associated with the magnetic damping.When the JLF-1steel is used as the blanket structural material of fusion reactors,the experimental data for tensile proper-ties,fracture toughness and fatigue crack propaga-tion beha v iors are v ery important to estimate a safety life in terms the critical crack length of a1Corresponding author.Tel.:'82-51-890-1642;fax:'82-51-890-2232E-mail address:hkyoon@dongeui.ac.kr (H.K.Yoon).Fusion Engineering and Design 61Á62(2002)677Á682www.else v /locate/fusengdes0920-3796/02/$-see front matter #2002Else v ier Science B.V.All rights reserved.PII:S 0920-3796(02)00099-6blanket with the irradiation [5,6].Howe v er,in spite of the widespread application of JLF-1steel in fusion reactor,our current understanding of fatigue life and fatigue crack propagation beha-v iors was still somewhat limited e v en though many in v estigations were performed of the low cycle fatigue life.Detailed studies of the micro-mechan-ism of high cycle fatigue life and fatigue crack propagation are needed because these in v estiga-tions ha v e been largely concerned with the low cycle fatigue of the RAFs (JLF-1,F82H)[7].The fatigue limit has historically been a prime con-sideration in long-life fatigue design.In case of the JLF-1material,the fatigue limit has an enormous range,depending on surface finish,specimen or component size,type of loading,temperature,corrosi v e and other aggressi v e en v ironments,re-sidual stresses,and stress concentration.In the fatigue crack propagation test,standard test methods ha v e been de v eloped for performing constant amplitude fatigue crack growth tests based on ASTM standard E647[8].Richards and Lindley [9]examined a broad range of ferrous materials and concluded that crack propagation rate associated with striation formation was in-sensiti v e to stress ratio.Departure from striation formation to include micro-clea v age and v oid coalescence or inter granular cracking was found to the accreditation of accelerated crack growth rates.It was generally accepted that the crackgrowth rates in the Paris law region (region II)were independent of stress ratio for medium-strength steels [10].In this paper,the high cycle fatigue life experi-ment ha v e been carried out for the stress ratio R 00at room temperature and 4008C.And fatigue crack propagation rate on the specimen of the full and half size at stress ratios of 0.1,0.3and 0.5were in v estigated.Fatigue crack propagation laws were presented by the assessment of the combined effects of the stress intensity factor range D K and stress ratio R .The effects of rolling direction and test temperature on fatigue limit stress,and the effects of stress ratio and test specimen size on the fatigue crack propagation beha v ior in JLF-1steel were also in v estigated.Table 1Chemical composition of JLF-1steel (wt.%)CSi Mn P S Al Cr W V Ta N Ti B BM0.10.050.450.0030.0020.0038.851.990.200.080.0231Á0.0002Normalizing:1323K )1h/A.C.,Tempering:1053K )1h/A.C.and heat treatment condition of JLF-1.Table 2Mechanical properties of JLF-1steel Material Test temperature (8C)Yield strength (MPa)Tensile strength (MPa)Elongation (%)BML R.T 48263027.8400Á51923.9BMTR.T 45160027.9400Á51922.5Fig.1.Specimen orientation adapted from JLF-1plate.H.K.Yoon et al./Fusion Engineering and Design 61Á62(2002)677Á6826782.Material and experimental proceduresThe chemical composition of the JLF-1steel plate (BM)is shown in Table 1.The plate with the thickness of 13mm was normalized at 1323K for 1h under the air cooling and then tempered at 1050K for 1h.The mechanical properties are gi v en in Table 2.The preparation of test specimens for e v aluating fatigue life and fatigue crack propagation of JLF-1steel is shown in Fig.1.The fatigue life test specimen has a diameter of 6mm as shown in Fig.2.The testing frequency was 10Hz at the stress ratio R 00.The fatigue crack propagation tests of JLF-1steel were performed using full size compact tension specimens and half size compact tension specimen as shown in Fig.3(a)and (b).All of the testing were carried outusing a computer controlled electro ser v o-hydrau-lic testing machine (MTS model 810),a load control mode,a constant load amplitude with stress ratio of 0.1,0.3and 0.5,a sinusoidal wa v e form and a frequency of 10Hz at room tempera-ture.The fatigue crack length were monitored using a compliance method and obser v ed using a tra v eling optical microscope with 0.001mm reso-lution.Fig.2.Dimension of fatigue life test specimen (unit:mm).Fig.3.Dimension of fatigue crack propagation test specimen (unit:mm).Fig.4.Relation between stress range and number of cycles to failure of JLF-1steel (BML,BMT)at R.T.H.K.Yoon et al./Fusion Engineering and Design 61Á62(2002)677Á6826793.Results and discussion 3.1.S ÁN cur v esS ÁN cur v es for the longitudinal (BML)and trans v erse (BMT)to the rolling direction at the room temperature and 4008C are presented in Fig.4and Fig.5,respecti v ely.At room tempera-ture,the fatigue limits of BML and BMT were 480and 490MPa at 1)107cycles,respecti v ely.Also,at 4008C,the fatigue limits of BML and BMT were 400,416MPa at 1)107cycles,respecti v ely.The fatigue strength of the BMT specimen was a little higher than the BML specimen at the room temperature and 4008C.At higher and lower stress le v els,the effects of rolling direction between BML and BMT were similar.It means that the base material of JLF-1steel showed the isotropic beha v ior in fatigue life properties of rolling direc-tion.The fatigue limits at 4008C is lower than those of room temperature at BML and BMT speci-mens.It is accredited by the decreasing of tensile strength under the en v ironment of high tempera-ture.3.2.Relation between da/dN and D KBelow D K th ,fatigue cracks are characterized as non-propagating cracks.Microstructure,mean stress,frequency,and en v ironment mainly controlregion I crack growth.Region II shows essentially a liner relationship between log d a /d N and log D K ,which corresponds to the formula sug-gested by Paris and Erdogan [11].d a =d N 0C (D K )mHere,m is the slope of the line and C is the coefficient found by extending the straight line to D K 01MPa m 0.5.The fatigue crack propagation beha v iors of the full and half size specimen,under the three stress ratios,R 00.1,0.3and 0.5using constant stress le v el are obser v ed,and those results are presented in terms of the fatigue crack propagation rate (d a /d N )according to the stress intensity factor range (D K )as shown in Figs.6and 7and Fig.8,respecti v ely.In this figures,the plot clearly shows the near-threshold high Paris and high D K regimes of each cur v e.The stable crack propagation was obser v ed at K max le v els below 50MPa m paring those figures,the full and half size specimen has few effects of stress ratios.Especially in the fatigue crack propagation rate of halfsizeFig.5.Relation between stress range and number of cycles to failure for JLF-1steel (BML,BMT)at 4008C.parison of fatigue crack propagation cur v es for full and half size specimen at stress ratio R 00.1.H.K.Yoon et al./Fusion Engineering and Design 61Á62(2002)677Á682680specimen,the effect of stress ratio was not shown in the high D K region e v en though the effect of stress ratio in the low D K region was shown a little bit.Without connection with stress ratios,the fatigue crack propagation of full size specimen shows a straight line,e v en though there were a little bit of scattering on the low D K le v el.The fatigue crack propagation beha v ior of high D K region has less influence of stress ratio than in low D K region.The exponents,m and constant,C of Paris for each stress ratio are presented in Table 3.3.3.Effects of specimen sizeBy comparing between result of full and half size specimen in Paris region (region II),we can recognize the effect of specimen size.All the results of the constant amplitude fatigue crack propaga-tion test on full and half size specimens are similar to each other at the each stress ratios.Therefore,it is belie v ed that the specimen size has no effect onthe fatigue crack propagation rate for JLF-1steel at room temperature.Although it is necessary to correct conclusion from the e v aluation of crack closure and fracture mechanics,it is belie v ed that the half size specimen can be e v aluated the fatigue crack propagation beha v iors from this studies.In the near future,D K eff considering crack closure will be defined to analyze the effect of specimen size.But,in this study,the data of full and half size specimen were similar to the results obtained from other studies of similar alloys [12,13].4.ConclusionsIn this study,the effects of rolling direction,the effects of test temperature on the fatigue life,the effects of the stress ratios,the effects of test specimen size on the fatigue crack propagation rate,the beha v ior of the fatigue life and fatigue crack propagation in JLF-1steel were in v estigated.Those results can be summarized asfollowing;parison of fatigue crack propagation cur v es for full and half size specimen at stress ratio R 00.3.parison of fatigue crack propagation cur v es for full and half size specimen at stress ratio R 00.5.H.K.Yoon et al./Fusion Engineering and Design 61Á62(2002)677Á682681(1)The fatigue limit stress of BML and BMT at the room temperature and 4008C were 480,400and 490MPa,416MPa at 1)107cycles,respec-ti v ely.It can be found that the base material showed the isotropic beha v ior in fatigue life by the effect of rolling direction and test temperature.(2)In the region II,the fatigue crack propaga-tion rate of full size specimen was not shown from the effect of stress ratios R 00.1,0.3and 0.5at room temperature.In case of the fatigue crack propagation rate of half size specimen,the effect of stress ratio was not shown in the high D K region e v en though the effect of stress ratio in the low D K region was shown a little bit.(3)The fatigue crack propagation rate of the half size specimen is similar to that of the full size specimen at the stress ratios of 0.1,0.3and 0.5.It can be concluded that the fatigue crack propaga-tion beha v ior of JLF-1steel can be e v aluated by using half size specimen.AcknowledgementsThis work was supported by Japan Society for the Promotion of Science and Brain Korea 21and Research Center for Electronic Ceramics of Don-geui Uni v ersity.The authors wish to thanks for the persons concerned.References[1]J.W.Da v is, D.J.Michel,Proceedings of the topicalconference on ferritic alloys for use in nuclear energy technologies,TMS-AIME,Snowbird,Utah,1984.[2]R.L.Klueh, D.S.Gelles,M.Okada,N.H.Packan,Reduced acti v ation materials for fusion reactors,ASTM-STP (1990)1047.[3]A.Kohyama,Y.Kohno,K.Asakura,H.Kauano,R&Dof low acti v ation ferritic steels fusion in Japanese Uni-v ersity,Journal of Nuclear Materials 212Á215(1994)684Á689.[4]K.Asakura,et al.,Mechanical properties and microstruc-ture changes of low acti v ation 3Cr Á2W ÁV ÁTi ferritic steels de v eloped for nuclear applications,ISIJ Interna-tional 30(11)(1990)947Á954.[5]Y.Kohno,A.Kohyama,T.Hirose,M.L.Hamilton,M.Marui,Mechanical property changes of low acti v ation ferritic/martensitic steels after neutron irradiation,Journal of Nuclear Materials 271Á272(1999)145.[6]A.Nishimura,N.Inoue,T.Muroga,Fracture toughnessof low acti v ation ferritic steel (JLF-1)weld joint at room temperature,Journal of Nuclear Materials 258Á263(1998)1242.[7]A.Nishimura,T.Nagasaka,N.Inoue,T.Muroga,C.Namba,Low cycle fatigue properties of a low acti v ation ferritic steel (JLF-1)at room temperature,Journal of Nuclear Materials 283Á287(2000)677Á680.[8]Standard Test Method for measurement of fatigue crackgrowth rates,ASTM E647,v ol.03.01,ASTM,West Conshohocken,PA,2000,pp.591.[9]C.E.Richard,T.C.Lindley,The influence of stressintensity and microstructure on fatigue crack propagation in ferritic materials,Engineering Fracture Mechanics 4(1972)951Á978.[10]C.Mercer, A.B.O.Soboyejo,W.O.Soboyejo,Micro-mechanisms of fatigue crack growth in a forged inconel 718nickel-based superalloy,Materials Science and En-gineering A 270(1999)308Á322.[11]P.C.Paris, F.Erdogan,A critical analysis of crackpropagation laws,Transactions ASME Journal of Basic Engineering 85(1963)528Á534.[12]J.E.Kong,Fatigue Engineering Material Structure 5(1982)177Á188.[13]B.A.Lerch,S.D.Antolo v ich,Material Transactions 21A(1990)2169Á2177.Table 3Variation of Paris exponent (m )and constant (C )with stress ratio(R )for JLF-1steel Stress ratio,RParis exponent,m Constant,C Full size specimenHalf size specimen Full size specimen Half size specimen 0.1 3.23 3.44 1.81E (09 6.89E (100.3 3.34 3.17 1.26E (09 1.92E (090.53.563.246.74E (102.15E (09H.K.Yoon et al./Fusion Engineering and Design 61Á62(2002)677Á682682。
Scaling of discrete dislocation predictions for near-threshold fatigue crack growth

eff (⌬Kth / E)2Ϸb, where b is the Burgers vector magnitude and E is the Young’s modulus. The normalized effective fatigue threshold ⌬Keff th / E for a variety of metallic alloys is plotted in Fig. 1 as a function of the normalized yield strength sY / E from the data in Kang et al. [7]: ⌬Keff th is seen to be reasonably independent of the yield strength over nearly two orders of magnitude variation in sY / E. A variety of continuum plasticity models have been proposed to rationalize the fatigue behavior in regimes (A) and (B). Usami and Shida [8] postulated that the fatigue threshold corresponds to a critical plastic zone size while Donahue et al. [9] proposed that the threshold for the onset of crack growth occurs when the crack tip opening displacement attains a value comparable to a critical microstructural parameter. Models for the Paris law regime include the geometric models of Laird and Smith [10] and of McClintock [11], which presume that crack growth rates are proportional to the crack tip opening displacement, and the damage accumulation models of Weertman [12] and Rice [13]. A feature of all these models is that they predict a dependence of the crack growth rates on the yield strength of the material in contrast to experimental observations. More recently, Nguyen et al.
ASTM材料与实验标准.E399

Referenced Documents Terminology
Stress-Intensity Factor Plane-Strain Fracture Toughness Crack Plane Orientation
Section 2 3 3.1.1 3.1.2 3.1.3
1 This test method is under the jurisdiction of ASTM Committee E08 on Fatigue and Fracture and is the direct responsibility of Subcommittee E08.07 on LinearElastic Fracture.
1
E 399 – 05
1.6 Specific requirements related to special test procedures:
Fatigue Precracking KIc Specimens Hot-Pressed Beryllium Testing Rapid-Force Testing
This standard has been approved for use by agencies of the Department of Defense.
1. Scope
1.1 This test method covers the determination of fracture toughness (KIc) of metallic materials under predominantly linear-elastic, plane-strain conditions using fatigue precracked specimens having a thickness of 1.6 mm (0.063 in.) or greater2 subjected to slowly, or in special (elective) cases rapidly, increasing crack-displacement force. Details of test apparatus, specimen configuration, and experimental procedure are given in the Annexes.
Initiation and propagation of fatigue cracks in cast IN 713LC superalloy

Initiation and propagation of fatigue cracks in cast IN 713LC superalloyL.Kunz a,*,P.Lukáša ,R.Konecˇnáb aInstitute of Physics of Materials,AS CR,Z ˇiz ˇkova 22,61662Brno,Czech Republic b Z ˇilina University,Department of Materials Engineering,Univerzitná1,Slovak Republica r t i c l e i n f o Article history:Received 14December 2009Received in revised form 31January 2010Accepted 3February 2010Available online 10February 2010Keywords:IN 713LC High temperature fatigue Casting defectsCrystallographic fatigue crack initiationMean stress effecta b s t r a c tFatigue life,initiation and propagation of cracks at 800°C in a cast Ni-base superalloyIN 713LC were experimentally studied in high-cycle fatigue region.Load symmetricalcycling and cycling with high tensile mean load were applied.Both crystallographic crackinitiation resulting in long Stage I crack growth and non-crystallographic Stage II propaga-tion were observed.High scatter of fatigue life data was explained by:(i)variability inmicrostructural conditions for crystallographic crack initiation and propagation and by(ii)influence of casting defect size distribution.The fractographic observation supportsthe slip band decohesion mechanism of crack initiation and an important role of cyclic sliplocalization in persistent slip bands.Ó2010Elsevier Ltd.All rights reserved.1.IntroductionFatigue crack initiation and early crack propagation resistance predestinate high-cycle fatigue (HCF)performance of engi-neering materials.These two periods of fatigue damage often represent the decisive part of the fatigue lifetime of compo-nents.Both the crack initiation and early crack propagation are highly sensitive to material microstructure.In most crystalline metals and alloys fatigue crack initiation occurs along crystallographic slip planes at an external surface [1].This mode of cracking has been called Stage I.The corresponding fatigue fracture surface (or fatigue crack length)is usually small and limited to one surface grain.Crack initiation and propagation in the Stage I take place along crystallographic slip planes having high cyclic resolved shear stress.The crack length at which the propagation mode changes from the crystallographic Stage I to the non-crystallographic Stage II depends mainly on material,temperature and the stress amplitude.Cyclic deformation and cyclic slip localization in Ni-base superalloys,which are f.c.c.with slip systems {111}h 110i occurs heterogeneously in planar bands lying along the crystallographic {111}planes.As a result,very often extensive long Stage I cracking is observed.Antolovich [2]summarizes that crystallographic Stage I crack propagation has been observed in both single crystal and polycrystal nickel-base superalloys.The extent of crystallographic crack propagation appears to be influenced by temperature [3]environment and frequency [4],and in the case of long cracks by stress intensity factor ampli-tude K a [5,6].Decisive role of the cyclic slip localization and initiation of cracks in slip bands was confirmed both for plain and notched bodies [7,8].However,the details of the mechanism and the role of the cyclic slip bands in the fatigue crack initiation and early crack propagation at high temperature in Ni-base superalloys is not fully elucidated.Conventionally cast polycrystalline Ni-base superalloy IN 713is an engineering material,which has been used in turbine industry since the fifties of the last century.Surprisingly,the high-cycle high temperature fatigue life data are quite rare in the open literature.The knowledge on the influence of mean stress on fatigue behaviour is even more limited;the only 0013-7944/$-see front matter Ó2010Elsevier Ltd.All rights reserved.doi:10.1016/j.engfracmech.2010.02.002*Corresponding author.Tel.:+420549246327;fax:+420541218657.E-mail addresses:kunz@ipm.cz (L.Kunz),lukas@ipm.cz (P.Lukáš),radomila.konecna@fstroj.uniza.sk (R.Konecˇná).L.Kunz et al./Engineering Fracture Mechanics77(2010)2008–20152009 available constant life diagram can be found in[9].On the other hand,fatigue behaviour of this material is the current con-cern of the leading European gas turbine producers;more detailed material data are necessary to improve the existing stan-dard design and prediction tools[10].A typical feature of HCF strength of cast superalloys is high scatter of fatigue life data.This effect is attributed to casting defects,microshrinkages and other inhomogeneities,which are often sites of the fatigue crack initiation.Their influence can be diminished by hot isostatic pressing technology.Its beneficial effect on fatigue performance was reported[11],however, the results often fall short of expectations.In the case of materials exhibiting various modes of fatigue crack initiation and early crack propagation one of the reasons for the large scatter may be the variability of conditions for crack initiation and early propagation.This work is focused on an investigation of HCF crack initiation,propagation and fatigue life of conventionally cast super-alloy IN713LC loaded at800°C in air in a symmetrical cycle and in an asymmetrical cycle with tensile mean stresses of300 and400MPa.The aim was to get a new set of experimental fatigue life data and to discuss and explain the observed large scatter in terms of crack initiation and propagation mechanisms.Based on fractographic observation and transmission elec-tron microscopy an alternative mechanism of decohesion model for fatigue crack growth in Ni-base superalloys was proposed.2.MaterialIN713LC was conventionally cast as rods of20mm in diameter and100mm in length.The chemical composition of the alloy studied is given in Table1.All cast rods were controlled by conventional X-ray defectoscopy with the resolution limit of 0.5mm.They were found‘‘defect free”in this sense.The microstructure of cast IN713LC is of dendritic nature.An example of a dendritic structure in transversal section of a cast rod is shown in Fig.1.The microstructure at higher magnification can be seen in Fig.2.The dendritic regions are char-acteristic byfine and homogeneous c/c0structure.Colonies of large c0particles,microshinkages and casting defects are pres-ent in the interdendritic regions.Casting defects as observed on a polished axial metallographical section of the gauge length of a specimen are shown in Fig.3.Their distribution is not uniform.They are often grouped and form clusters.In the three-dimensional space the defects form interconnected systems.3.ExperimentalHigh temperature fatigue tests were conducted on cylindrical button end specimens with35mm gauge length and5mm in diameter.The specimen gauge length wasfine ground.Tests were performed at800°C in laboratory air at controlled load in a100kN resonant testing machine.The frequency of sine wave loading was105±3Hz.The start-up procedure of a test consisted of heating up the specimen at controlled zero load.One hour after the desired temperature was reached the mean stress has been applied within some seconds and subsequently the resonant system was switched on.The load amplitude was reached during a ramp of a length of about500cycles.Fracture surfaces were examined by means of scanning electron microscopy(SEM).Axial sections through the fracture surface were prepared,metallographically polished,etched and observed by means of light microscopy.Transmission elec-tron microscopy(TEM)on thin foils was applied for observation of dislocation structure.4.ResultsExperimentally determined fatigue life(in terms of S–N points)for loading with zero mean load and with tensile load corresponding to the initial mean stresses r mean=300and400MPa is shown in Fig.4.The open points with arrows indicate run out specimens.The following conclusions can be drawn:the increase of tensile mean stress from0to300MPa results in a considerable shift of S–N points to lower stress amplitudes for given number of cycles.Further increase of r mean to400MPa has weaker effect.The S–N data in Fig.4exhibit very large scatter.In the case of the stress symmetrical loading at the stress amplitude180MPa,one specimen failed at6.5Â104cycles,whereas another specimen at the same stress amplitude level did not fail after2.5Â107cycles,which is a difference of more than three orders of magnitude.Similar scatter can be ob-served also for loading with mean stresses.Two types of fatigue crack initiation and propagation were recognized on fracture surfaces of failed specimens.Thefirst type is shown in Fig.5.The fracture surface corresponds to the specimen failed after loading with r mean=300MPa and stress amplitude r a=120MPa.The crack initiates obviously on a large internal casting defect,which is clearly visible on the frac-ture surface.The macroscopic crack plane is nearly perpendicular to the principal rge‘‘fish eye”surrounding the defect is obvious.There are distinct traces of the dendritic structure on the non-crystallographic fracture surface within thefish eye.Thefigure indicates that the crack surface appearance suddenly changes when the internally propagated crack reaches the surface of the specimen.At this moment the laboratory atmosphere interfered with the freshly created fracture surface.The near vicinity of the casting defect in another specimen with similar failure is shown in Fig.6.The fracture surface is again of non-crystallographic nature.The dendritic structure,coarse c0precipitates and small casting porosity in interden-dritic regions can be identified(right upper corner in Fig.6).The second type of crack initiation and early crack propagation is shown in Fig.7.The fracture surface corresponds to the specimen loaded at r mean=300MPa and r a=130MPa.Systems offor mean stress0MPa and tensile mean stresses of300and400large casting defect in its centre.r mean=300MPa and r a=plain crystallographic facets in the place of internal crack initiation can be seen.They are either parallel(facets labeled2,3 and4in Fig.7)or inclined mutually at high angles;this holds,e.g.for facet1and2.At low magnification,as observed by light microscopy,the facets have high reflexivity and mirror like appearance.At high magnification decohesion of material alongthe facets can be often observed.Arrows in Figs.7and8denote this decohesion.The direction of observation in Fig.8was chosen in such a way that the facet on the right hand side was at low angle to the direction of observation and the facet onL.Kunz et al./Engineering Fracture Mechanics77(2010)2008–20152013Further,it can be seen that the facets terminate at the grain boundaries.Connecting non-crystallographic fatigue fracture surface in neighbouring grains exhibits substantially higher roughness.An example of dislocation structure of fatigued IN 713LC with tensile mean stress as observed by TEM is shown in Fig.12.Two clear visible straight planar cyclic slip bands along the two non-parallel traces of {111}crystallographic planes inter-sect the c /c 0structure.The bands are very thin.Well developed slip bands obviously intersecting the c 0particles separated by c channels can be seen in Fig.13.The bands in this figure seem to be cracked.The dislocation density in the bands is high whereas in the rest of material is very low.5.DiscussionNi-base superalloys exhibit low stacking fault energy,which makes the cross-slip difficult.This expresses itself by planar deformation and by development of intense cyclic slip bands.Highly inhomogeneous dislocation arrangement was observed by Petrenec et al.[12]in IN 713LC loaded at 800°C.Planar arrangements in the form of bands parallel to the {111}planes develop at low-cycle fatigue (LCF)loading under controlled strain.The bands appear as thin slabs of high dislocation density cutting both the c channels and c 0precipitates.The presence of mean stress influences the development of slip bands in Ni-base alloys.LCF at 850°C does not produce the slip bands in Ni-base superalloy single crystals CMSX-4[13],whereas addi-tion of small cyclic component to large static stress leads to formation of slip bands [14].From Figs.12and 13it is obvious that the high dislocation density slip bands in IN 713LC form at 800°C under presence of tensile mean stresses in HCF region.The foil was prepared from a specimen which failed after loading with r mean =300MPa and r a =130MPa after 1.5Â107cy-cles.Fig.13shows the slip bands,which look like cracked.It cannot be excluded that the slots in bands come from more intense etching of highly deformed areas when the foil was prepared.Nevertheless,it seems to be a strong witness of the fact that the bands are ‘‘weakened”volumes in material.The observation of crystallographic facets on fracture surfaces dem-onstrates decohesion between facets,Figs.7and 8.The neighbouring facets are mutually fully separated.The separation dis-tance is of some microns and is of the same extent over the whole facet.As regards the mode of crack propagation in Ni-base polycrystals and single crystals there is a general agreement that both the crystallographic Stage I and the non-crystallographic Stage II take place and that their occurrence is a function of temperature,environment,frequency of loading and the crack growth rate.The majority of studies was performed on long cracks,e.g.[6,15].The detailed mechanisms of crack growth in both stages are not completely clear though the general fea-tures of fatigue crack propagation in f.c.c.metals were summarized many years ago [16].For Ni-base single crystals Duquette et al.[17]proposed a decohesion model based on weakening of slip planes coplanar with the crack tip.Subsequent failure,starting at a surface-connected pore proceeds by a combination of local normal and shear stress.The crack propagates along the {111}crystallographic plane.The decohesion model considers a continuous crack growth along the slip plane with increasing crack length.Our observation of decohesion of facets combined with observation of weakened slip bands by TEM indicates an alternative mechanism:HCF loading develops ‘‘weak”slip bands intersecting the whole grain,along which the material separates due to cyclic slip on non-coplanar slip systems in neighbouring grains.The occurrence of uniformly separated surfaces along the slip planes,Fig.8supports this alternative mechanism.Irrespective of the details of the mechanism of decohesion,after sufficiently high number of loading cycles interior inter-nal cracks along {111}planes develop.Their dimension and orientation depends on the variability of microstructure and the grain size of particular specimen.Planar cracks,which are inclined at various angles to the loading direction,once developed,serve later on in the fatigue process as starters of the final crack,which propagates internally by the non-crystallographic Stage II and forms the fish eye.The number of cycles necessary for the development of planar cracks varies according to the particular microstructural conditions.Because the stress intensity factors are different subsequent crack growth can dif-fer in crack propagation rate.The final impact is scatter in HCFlifetime.L.Kunz et al./Engineering Fracture Mechanics77(2010)2008–20152015 From the fractographic analysis it is evident that facets can be often found in areas adjacent to large casting defects,which form interconnected systems.The reason for it is their stress concentration effect.They increase the local stress amplitude, promote the slip on adjacent slip planes and contribute to the decohesion process.The defects contribute to the scatter of fatigue life data in this way because they have different stress concentration factor due to their different shape.The distribution of casting defects is probabilistic,which means that in some specimens extraordinary large defects or their agglomerates can occur.They initiate cracks due to their stress concentration effect in similar way as the isolated ones. However,once the crack is initiated at large defect agglomerate,it propagates with a rate determined by the stress intensity factor amplitude K a corresponding to the crack length including the defect dimension.If this is of the order of some tens of millimetres,the K a value may be sufficiently high to promote the Stage II propagation from the very beginning.However,the present state of knowledge does not allow to predict quantitatively the defect size(under given loading conditions)which reduces the Stage I cracking.Further research and reasoning of conditions of transition Stage I/Stage II is necessary.An exam-ple of the Stage II propagation from the defect is shown in Fig.5.The loading parameters were the following:r mean=300M-Pa,r a=120MPa and the number of cycles to failure1.19Â105.On the other hand,at the same mean stress,at even a slightly higher stress amplitude r a=130MPa,but in the absence of a large casting defect,the crystallographic initiation and prop-agation by Stage I took place,Fig.7,which resulted in more than one order of magnitude higher number of cycles to failure, namely4.1Â106.6.Conclusions1.Tensile mean stresses of300and400MPa reduce the high-cycle fatigue strength of IN713LC alloy at800°C when com-pared to the symmetrical loading.The S–N data exhibit a scatter more than three orders of magnitude.2.Fatigue fracture surface is either non-crystallographic,corresponding to the Stage II crack propagation or crystallographic,corresponding to the Stage I cracking.Both types of crack propagation can be found in a broad interval of mean stresses and stress amplitudes.3.Casting defects play an important role in fatigue crack imitation and early propagation.4.High scatter of fatigue life can be explained by:(i)variability of microstructural conditions for development of slip bandsand related crystallographic crack initiation and(ii)by the influence of casting defect size distribution. AcknowledgementsThis work was supported by the Project FT-TA4/023of the Ministry of Industry and Trade of the Czech Republic and the Project1QS200410502of the Academy of Sciences of the Czech Republic.This support is gratefully acknowledged. References[1]Klesnil M,LukášP.Fatigue of metallic materials.Prague:Academia/Elsevier;1992.[2]Antolovich BF.Fatigue and fracture of nickel-base superalloys.In:Lampman SR,Davidson GM,Reidenbach F,Boring RL,Hammel A,Henry SD,Scott JrWW,editors.ASM handbook fatigue and fracture,vol.19.Materials Park:ASM Int;1996.p.860.[3]Chu Z,Yu J,Sun X,Guan H,Hu Z.High cycle fatigue behaviour of a directionally solidified Ni-base superalloy DZ951.Mater Sci Engng2008;A496:355–61.[4]Leverant GR,Gell M.The influence of temperature and cyclic frequency on the fatigue fracture of cube oriented nickel-base superalloy single crystals.Metall Trans1975;6A:367–71.[5]Yu W,Yuan J,Wang Z.A study of fatigue fracture surfaces on a cast nickel-base superalloy.Fatigue Fract Engng Mater Struct1987;9:425–34.[6]King JE.Fatigue crack propagation in nickel-base superalloys–effects of microstructure,load ratio,and temperature.Mater Sci Technol1987;3:750–64.[7]Ren W,Nicholas T.Notch size effects on high cycle fatigue limit stress of Udimet720.Mater Sci Engng2003;A357:141–52.[8]LukášP,Kunz L,Svoboda M.High-temperature ultra-high cycle fatigue damage of notched single crystal superalloys at high mean stress.Int J Fatigue2005;27:1535–40.[9]Kunz L,LukášP,Mintách R,Hrbácˇek K.Effect of mean stress on high-cycle fatigue strength of IN713LC superalloy.Kovove Mater2006;44:275–81.[10]Transport Research Knowledge Centre[Internet].</web>[updated2008August1;cited2009December7].[11]Donachie MJ,Donachie SJ.Superalloys:a technical guide.2nd ed.Materials Park,OH:ASM Int;2002.[12]Petrenec M,Obrtlík K,Polák J.Inhomogeneous dislocation structure in fatigued Inconel713LC superalloy at room and elevated temperatures.Mater SciEngng2005;A400–401:485–8.[13]Obrtlík K,LukášP,Polák J.In:Rie KT,Portella PD,editors.Low cycle fatigue and elasto-plastic behaviour of materials.Amsterdam:Elsevier;1998.p.33–8.[14]LukášP,Kunz L,Svoboda M.High cycle fatigue of superalloy single crystals at high mean stress.Mater Sci Engng2004;A387–9:505–10.[15]Crompton JS,Martin JW.Crack growth in a single crystal superalloy at elevated temperature.Metall Trans1984;15A:1711–9.[16]McEvily Jr AJ,Boettner RC.On fatigue crack propagation in f.c.c.metals.Acta Metall1963;11:725–43.[17]Duquette DJ,Gell M,Pieto JW.A fractographic study of Stage I fatigue cracking in a nickel-base superalloy single crystal.Metall Trans1970;1:3107–15.。
Fatigue crack propagation of 444 stainless steel welded joints in air and in 3%NaCl aqueous solution

Fatigue crack propagation of 444stainless steel weldedjoints in air and in 3%NaCl aqueous solutionMasayuki Akita a ,Masaki Nakajima b ,Keiro Tokajia,*,Toshihiro ShimizubaDepartment of Mechanical and Systems Engineering,Faculty of Engineering,Gifu University,1-1Yanagido,Gifu 501-1193,JapanbDepartment of Mechanical Engineering,Toyota College of Technology,2-1Eisei-cho,Toyota 471-8525,JapanReceived 10May 2004;accepted 1October 2004Available online 8December 2004AbstractFatigue crack propagation (FCP)was studied on ferritic stainless steel welded joints in air and in 3%NaCl aqueous solution.In air,when the crack propagated normal to the weld line,FCP rates decreased temporarily as it reached the heat affected zone (HAZ)and then increased monotonously.When the crack propagated within HAZ and the weld metal,FCP rates were lower than those of the base metal.After allowing for crack closure,the FCP data of all the welded specimens became similar and coincided with those of the base metal.In 3%NaCl aqueous solution,all the welded specimens still showed enhanced FCP rates at high effective stress intensity factor range region,where extensive intergranular and quasi-cleavage fractures were seen.Ó2004Elsevier Ltd.All rights reserved.Keywords:Ferrous metals and alloys;Welding;Fatigue1.IntroductionFerritic stainless steels posses an excellent resistance to stress corrosion cracking (SCC),while they had poor toughness and as-welded ductility.In recent years,new ferritic stainless steels with extremely reduced (C +N)content have been developed,in which toughness and weldability are significantly improved [1,2].Of various joining methods,welding is widely used in machine components and structures.To ensure their safety and reliability,evaluation on the fatigue properties of welded joints is particularly important because they are very sensitive to fatigue loading.Although studies on corrosion fatigue behaviour [3]and fatigue crack ini-tiation and small crack growth [4]have been indicated in ferritic stainless steels themselves,there have been very limited studies on the fatigue behaviour of welded joints.Only a few studies on the toughness of welded joints have been reported [2,5].In addition,since stainless steels are mostly used in applications where corrosion resistance is required,it is also necessary to understand their fatigue behaviour in corrosive environments.In the present study,fatigue crack propagation (FCP)behaviour for large cracks was studied on welded joints of a ferritic stainless steel,type 444,in air and in 3%NaCl aqueous solution.The obtained results were discussed on the basis of residual stress,crack closure behaviour and fracture surface analysis.2.Experimental details 2.1.Material and specimensThe base metal is a ferritic stainless steel,type 444(18Cr–2Mo)whose chemical composition (mass %)is C:0.004,Si:0.06,Mn:0.1,P:0.024,S:0.006,Ni:0.11,Nb:0.17,Cr:18.72,Mo:1.81,V:0.06,N:0.068.The0261-3069/$-see front matter Ó2004Elsevier Ltd.All rights reserved.doi:10.1016/j.matdes.2004.10.004*Corresponding author.Tel.:+81582932500;fax:+81582301892.E-mail address:tokaji@cc.gifu-u.ac.jp (K.Tokaji)./locate/matdesMaterials and Design 27(2006)92–99Materials &Designmaterial was used in the as-received condition.The mechanical properties for two directions parallel and perpendicular to the rolling direction(L and T direc-tions,respectively)are listed in Table1.The proof stress and tensile strength in the T-direction are slightly higher than those in the L-direction.Fig.1shows the configuration of compact type(CT) specimens used in FCP experiment.As illustrated schemat-ically in Fig.2,three types of welded CT specimens were evaluated:the specimens of which starter notch was intro-duced perpendicular to the weld line(N-specimen,Fig. 2(a)),within the heat affected zone(HAZ)(H-specimen, Fig.2(b)),and within the weld metal(W-specimen,Fig. 2(c)).Since the welding direction was parallel to the T-direc-tion,the FCP direction was the L-direction in the N-speci-mens,while the T-direction in the H and W specimens. 2.2.Welding conditionWelding was performed by the tungsten–inert gaswelding method(TIG)with a root opening of1.6mm, an X-shape groove,the voltage of20V and three weld-ing passes on both sides.Thefiller metal was a309L austenitic stainless steel.The microstructures in the base metal,HAZ and the weld metal are represented in Fig.3.The microstructure of the base metal consists of ferritic grains with the aver-age size of approximately56l m(Fig.3(a)).In HAZ,the microstructure also consists of ferritic grains,but a pro-nounced grain growth takes place,resulting in the aver-age size of123l m(Fig.3(b)).On the other hand,the weld metal has a complicated microstructure:dendrite or acicular microstructure(Fig.3(c)).Hardness was measured using a Vickers hardness tes-ter and the obtained results were162HV,172HV and 194HV for the base metal,HAZ and the weld metal, respectively.2.3.ProceduresFCP tests were performed at a stress ratio,R,of0.05 using a19.6kN capacity electro-hydraulic fatigueTable1Mechanical properties of base metalDirection0.2%Proof stressr0.2(MPa)Tensile strengthr B(MPa)Breaking strength onfinal area r T(MPa)Elongationu(%)Reduction of areaw(%)L29344514803483T31046013523181M.Akita et al./Materials and Design27(2006)92–9993testing machine operating at a frequency of 1Hz.Test environments employed were laboratory air and 3%NaCl aqueous solution.The solution was kept at 30°C and circulated between the corrosion cell attached to the specimen surface and a reserved tank by using a pump.Crack length was monitored with a travelling micro-scope with a resolution of 10l m and crack closure was measured by an unloading elastic compliance method [6]using a strain gauge mounted on the back face of the specimen.After experiment,fracture surfaces were examined in detail using a scanning electron microscope (SEM).3.Results3.1.Residual stress distributionResidual stress in the welded specimens was measured by the X-ray diffraction method.Fig.4shows the distribu-tion of residual stresses normal to the FCP direction in the N-specimens.Residual stresses are approximately from À110to À480MPa at the top surface (the side of the firstpass),while À100to À500MPa at the bottom surface (the opposite side of the second pass).Compressive residual stresses decrease as the distance from the notch root in-creases toward the weld zone.From this measured resid-ual stress distributions,it is believed that large tensile residual stresses would be present in the weld metal.Residual stresses normal to the weld line were also measured in HAZ,which were approximately À300MPa (compression)at the top surface,while 100MPa (tension)at the bottom surface,regardless of the dis-tance from the weld zone.3.2.FCP behaviour of base metalAs described previously,the FCP direction is the L-direction in N-specimens,while the T-direction in H and W specimens,thus FCP behaviour for the base me-tal was evaluated using CT-specimens of both T–L and L–T orientations.Fig.5(a)represents the relationship between FCP rate,d a /d N ,and stress intensity factor range,D K ,for the base metal in air and in 3%NaCl aqueous solution.As can be seen in the figure,the effect of orientation is not seen at high D K region in both environments,but the FCP rates for the L–T orientation are faster than those for the T–L orientation at low D K region.It is worth noting that the FCP behaviour for both orienta-tions is affected by corrosive environment at D K P 15MPa m 1/2,where the FCP rates in 3%NaCl aqueous solution are significantly faster than those in air.When the FCP data are characterized in terms of the effective stress intensity factor,D K eff(Fig.5(b)),the dif-ference in FCP rate between both orientations observed in the d a /d N –D K relationship disappears.This indicates that crack closure played a significant role in FCP behaviour.Based on observation of crack path and frac-ture surface analysis,fracture surface roughness was considerably larger in the T–L orientation than in the L–T orientation at low D K region,thus it is believed that the difference in crack closure was induced from fracture surface roughness.It should be noted that the enhanced FCP rates in 3%NaCl aqueous solution observed in the d a /d N –D K relationships are still seen.This indicates that there ex-ists an environmental effect on FCP behaviour.As anFig.3.Microstructures:(a)base metal,(b)heat affected zone (HAZ),(c)weld metal.94M.Akita et al./Materials and Design 27(2006)92–99example,Fig.6reveals SEM micrographs of fracture surfaces in air and 3%NaCl aqueous solution.At low D K region,the appearance of fracture surfaces is similar in both environments,but at high D K region some inter-granular fracture can be seen on the fracture surface in 3%NaCl aqueous solution.3.3.FCP behaviour of welded jointsThe FCP behaviour for the N,H and W specimens is shown in Figs.7–9,respectively.For comparison,the FCP behaviour for the base metal is also included in those figures.N-specimen (Fig.7)In air,the FCP rates are nearly the same as those for the base metal in low D K region.With increasing crack growth,fluctuation of FCP rate becomes pronounced and FCP rates decrease temporar-ily around D K =20MPa m 1/2,then increase and tend to approach the FCP behaviour for the base metal.Such a complicated FCP behaviour appears to be due to resid-ual stress and hardness changes induced by welding.In 3%NaCl aqueous solution,the FCP rates are con-siderably lower than those for the base metal and fluctu-ation of FCP rate is not seen,being due to a higher initial D K level employed in the experiment.Fig.6.SEM micrographs showing fracture surfaces of base metal.M.Akita et al./Materials and Design 27(2006)92–9995H-specimen(Fig.8)In air,the FCP rates are lower than those for the base metal,particularly in low D K re-gion and with increasing D K gradually approach and then coincide with the FCP rates for the base metal at high D K region.This indicates a higher FCP resistance of HAZ than the base metal.In3%NaCl aqueous solution,the FCP rates are fas-ter than those in air,which becomes more pronounced with increasing D K.When compared with the data for the base metal,the FCP rates are lower in the entire D K region,particularly remarkable at low D K region.W-specimen(Fig.9)The overall FCP behaviour is similar to that of H-specimens.In air,the FCP rates are considerably lower than those for the base metal in low D K region,then gradually approach and eventually coincide with the FCP rates for the base metal at high D K region.This also indicates a higher FCP resistance of the weld metal than the base metal.In3%NaCl aqueous solution,the FCP rates are nearly consistent with those in air at low D K region, but become faster with increasing D K.When compared with the data for the base metal,the FCP rates are sig-nificantly lower in low D K region and then rapidly in-crease and coincide with the FCP rates at high D K region.3.4.Fracture surface analysisSEM micrographs of fracture surfaces in air are shown in Fig.10.As can be seen in thefigure,the oper-ative micromechanisms are the same in all the welded specimens:ductile transgranular at low D K region,while striation at high D K region.On the other hand,fracture micromechanisms oper-ated in3%NaCl aqueous solution were different from those in air and will be discussed later.4.Discussion4.1.Factors influencing FCP behaviour of welded joints in airAs seen in Fig.7,in air the N-specimens showedfluc-tuations of FCP rate and a remarkable decrease in FCP rate around D K=20MPa m1/2.It has been well known that residual stress plays a significant role in the FCP behaviour of welded joints.Fig.11represents the FCP behaviour and residual stress distribution in the N-spec-imens as a function of crack length in both environ-ments.It should be noted that the remarkable decrease of FCP rate in air occurs as the crack reaches HAZ. On the other hand,compressive residual stresses de-crease monotonously with increasing crack length,indi-cating that the residual stress distribution does not correspond to the remarkable decrease in FCP rate just before reaching HAZ.The similar results have been re-ported in laser welded butt joints,which was due to a sudden hardness change at the boundary between the base metal and HAZ[7].At low D K region,in spite of the presence of compressive residual stresses,the FCP rates for the welded specimens are nearly the same as those for the base metal(see Fig.7),this is because the compressive residual stress of approximatelyÀ270 MPa was detected in the base metal,which is equivalent96M.Akita et al./Materials and Design27(2006)92–99to the compressive residual stresses in the welded specimens.The results in3%NaCl aqueous solution did not showcomplicated FCP behaviour as seen in air.This is due to a higher initial D K level employed in the experiment, thus the effect of HAZ becomes relatively small.In the H and W specimens,the cracks propagated within HAZ and the weld metal,pres-sive residual stress of approximatelyÀ300MPa and ten-sile residual stress of100MPa were present at the top and bottom surfaces in HAZ,respectively.Residual stress in the weld metal could not be measured,but it is assumed that similar residual stresses would beFig.10.SEM micrographs showing fracture surfaces of all welded specimens in air.M.Akita et al./Materials and Design27(2006)92–9997present.Although it is not easy to understand the effect of residual stress in such a case,pressive on one side and tensile on the opposite side,it seems that the FCP behaviour is affected by compressive residual stress rather than tensile residual stress,because the absolute value of the former is significantly larger than that of the latter.In addition to residual stress,deflection of crack path was much more pronounced in HAZ and the weld metal due to grain growth and solidification microstructure,respectively,which also contributes the higher FCP resistance of HAZ and the weld metal than the base metal.4.2.FCP behaviour after allowing for crack closure The FCP behaviour characterized in terms of D K effis shown in Fig.12.As can be seen in the figure,in air the d a /d N –D K effrelationships for all the welded specimens are almost identical to that of the base metal.Therefore,the differences among the welded specimens and be-tween the welded specimens and the base metal observed in the d a /d N –D K relationships are attributed to crack closure that was induced by residual stress and fracture surface roughness.In 3%NaCl aqueous solution,the d a /d N –D K effrela-tionships in all the welded specimens are nearly the same,thus the difference among the welded specimens observed in the d a /d N –D K relationships is also attrib-uted to crack closure.However,when compared with the d a /d N –D K effrelationships in air,the FCP rates in 3%NaCl aqueous solution are significantly faster in the region of D K eff>15–20MPa m 1/2,which indicates that an environmental effect exists in this region.4.3.Effect of corrosive environment on FCP behaviour of welded jointsAs seen in Fig.12,the FCP rates of all the welded specimens were still faster at high D K effregion in 3%NaCl aqueous solution,suggesting that operative micromechanisms would be different from in air.Therefore,fracture surfaces were examined in detail using SEM.SEM micrographs of fracture surfaces at high D K region where the enhanced FCP rates were observed are shown in Fig.13.At low D K region where the same FCP rates were observed in both environments,the fracture surfaces in 3%NaCl aque-ous solution revealed ductile transgranular,which was the same as in air.At high D K region,however,a significant fraction of intergranular fracture or quasi-cleavage fracture can be seen (Fig.13),indicat-ing clearly that different fracture micromechanisms from in air have operated in 3%NaCl aqueous solution.SCC,hydrogen embrittlement and intergranular cor-rosion are believed to be the possible causes of brittle nature in 3%NaCl aqueous solution.However,the effect of SCC would be negligible,because it has been indi-cated that ferritic stainless steels had very low suscepti-bility to SCC even in a highly concentrated chloride solution [8].In order to confirm the resistance to SCC of the present 444stainless steel,SCC tests have been performed using CT-specimens in 3%NaCl aqueous solution,but SCC did not take place.On the other hand,it has been pointed out that hydrogen embrittlement oc-curred under cathodic potentials in high purity ferritic stainless steel [9].However,hydrogen embrittlement would not take place in the present case,because of a low hydrogen-produced environment,i.e.3%NaCl aqueous solution.Therefore,it is believed that inter-granular corrosion would be the cause for the enhanced FCP observed in 3%NaCl aqueous solution,because it has been indicated that HAZ became sensitive to inter-granular corrosion in ferritic stainless steel weldments [8],and thus welded joints would have increasing pro-pensity of intergranular fracture compared with the base metal.The weld metal is an austenitic stainless steel,type 309L,which also showed enhanced FCP at high D K effregion.This would be attributed to hydrogen embrittle-ment of martensitic phase transformed from austenitic phase [10].Fig.13.SEM micrographs showing fracture surfaces of all welded specimens in the FCP regime enhanced by 3%NaCl aqueous solution.98M.Akita et al./Materials and Design 27(2006)92–995.ConclusionsFatigue crack propagation(FCP)behaviour for large cracks was studied on welded joints of a ferritic stainless steel,type444,in air and in3%NaCl aqueous solution.The obtained results were discussed on the basis of residual stress,crack closure behaviour and fracture surface analysis.The conclusions can be made as follows:(1)In air,the welded specimens of which FCP direc-tion was perpendicular to the weld line showed a complicated FCP behaviour with frequentfluctua-tions of FCP rate.When the crack reached HAZ, the FCP rates were significantly decreased and then monotonously increased.When the cracks propa-gated within HAZ and the weld metal parallel to the weld line,the FCP rates for both specimens were almost identical and lower than those for the base metal in the entire D K region.(2)The FCP rates of all the welded specimens in3%NaCl aqueous solution were enhanced com-pared with those in air,being more pronounced with increasing D K.(3)In air,after allowing for crack closure,all thewelded specimens showed nearly the same FCP behaviour,indicating that the observed differences in the FCP rate characterized in terms of D K were attributed to crack closure.(4)The FCP rates in3%NaCl aqueous solution werestill faster at high D K effregion than those in air after allowing for crack closure,where extensive inter-granular fracture or quasi-cleavage fracture was seen.AcknowledgementsThe authors thank Mr.Y.Asano,Mr.T.Hayakawa, Mr.M.Itoh and Ms.C.Ohmori for their experimental assistance.References[1]Nakazawa T,Suzuki S,Sunami T,Sogo Y.Application of high-purity ferritic stainless steel plates to welded structures.ASTM STP1980;706:99–122.[2]Redmond JD.Toughness of18Cr–2Mo stainless steel.ASTMSTP1980;706:123–44.[3]Kimura Y,Yagasaki Y,Kunio T.Initiation process of corrosionfatigue cracks in stainless steels.Trans Jpn Soc Mech Eng 1984;A50-1:33–40.[In Japanese].[4]Nakajima M,Akita M,Tokaji K,Shimizu T.Fatigue crackinitiation and early growth behavior of a ferritic stainless steel in laboratory air and in3%NaCl aqueous solution.JSME Int J,Ser A2003;46–4:575–81.[5]Krysiak KF.Weldability of the new generation of ferritic stainlesssteels-update.ASTM STP1980;706:221–40.[6]Kikukawa M,Jono M,Tanaka K,Takatani M.Measurement offatigue crack propagation and crack closure at low stress intensity level by unloading elastic compliance method.J Soc Mater Sci Jpn 1976;25:899–903.[In Japanese].[7]Minagi A,Tokaji K.Fatigue crack propagation of laser weldedbutt joints.Fracture mechanics:applications and challenges.In: Proceedings of the13th european conference on fracture (ECF13).San Sebastian,Spain;2000[CD-ROM].[8]Kowaka M.The corrosion behavior of ferritic stainless steels.JSoc Mater Sci Jpn1974;23:924–35.[In Japanese].[9]Koterazawa K,Uchida H,Ohshiba H.Effect of tensile orientationon hydrogen embrittlement in single crystals of high purity ferritic stainless steel.J Soc Mater Sci Jpn1993;42:983–9.[In Japanese].[10]Endo K,Komai K,Murayama S.Influence of ClÀconcentrationon corrosion fatigue crack growth of an austenitic stainless steel.Trans Jpn Soc Mech Eng1982;48:1489–95.[In Japanese].M.Akita et al./Materials and Design27(2006)92–9999。
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were machined from a production railway axle of Chinese LZ50 axle steel. Chemical composition of the material (wt %) is 0.52 C, 0.74 Mn, 0.26 Si, 0.07 Cr, 0.03 Ni, 0.03 Cu, 0.036 Al, 0.001 S, 0.007 P, and the residual Fe. Monotonic mechanical properties at room temperature are 705 MPa ultimate strength, 385 MPa 0.2% proof strength, 25 % elongation, and 50 % reduction of area. Average conventional fatigue limit corresponding to the life of 107 a.
Fig. 1. Specimen geometry for the present study. Fig. 2. Metallurgical photograph of 5# specimen. Before testing, the test pieces of specimens were polished into mirror finish and then were etched with a solution of 25 ml HNO2 + 75 ml HCl to reveal the material microstructures. Metallurgical photograph for 5# specimen is given in Fig. 2. It reveals that microstructures are consist of web like ferrites and layered pearlites. Using Auto Montage photograph analysis system to treat the photo, it indicates that the ferrites have an equivalent diameter range of 1.1 to 21.6 mum and an average value of 9.1 mum. While the pearlites are distributed with an equivalent diameter range of 1.67 to 24.85 mum and an average value of 17.04 mum. Experiments. Full reversed fatigue tests with the stress ratio of -1 were performed on Rumul 25 t test machine at room temperature under a sine wave loading mode with the frequency of around 100 Hz. Stress ranges were between 170 and 200 MPa which is lower than the material conventional fatigue limit of around 230 MPa with 107 stressing cycles, close to the real service condition of the production axle. The short crack behaviour was observed with a replicating technique. Fatigue tests were interrupted at set time intervals in order to replicate the specimen surfaces. The intervals are relatively short during the test initial piece so as to obtain more detailed micro-cracks information in the MSC regime. Number of replicating actions for each specimen is around 10 to 15. when replicating about 10 MPa tensile stress was maintained to help keep the cracks open and then two 5×20 mm acetate strips were progressively pasted on the opposite parts of the specimens. Crack Originations Checking. After testing, fracture surface of a specimen was checked using SEM to determine the initial locations of the ESFCs result in the specimen failure. Result indicates that the ESFCs were all initiated from the surfaces of specimens. Combining the following surface cracks observations, it cleans that the ESFCs were almost initiated from the material weaker phase, the weakest surface ferrite particles. Cracks Observations. After testing, the dried replicas were examined using an integrated computer system of combining an optical microscope, a digital formed photographs, and the β2 2á Auto-Montage graphs analysis. To avoid differences of the test data resulting from β θ 1 magnifications in observations, detectable size of the micro-cracks on each replica was kept to about 5 to 10 mum. In accordance with the above mentioned “effective short fatigue theory”, a “reversed observed policy” was applied to obtain Fig. 3. Four elements for each micro-crack. information of the micro-cracks:
2
Chemistry Research Institute, China Academy of Railway Sciences, Beijing 100081
a
yxzhao@, bhezhong@, cyb@
Keywords: Railway; Axle; Fatigue; Threshold; Short crack.
Abstract. Collective short fatigue behaviour nearby material micro-structural barrier threshold is experimentally observed for the smooth specimens of Chinese railway LZ50 axle steel. Effective micro-cracks which result in the specimens’ failure were initiated from the material ferrite particles on the surfaces of the specimens. Four elements i.e. crack size, orientation angle, and the two crack tip orientation angles should be contained for each micro-crack. The collective micro-crack behaviour should be described by an equivalent dominant effective short fatigue crack (ESFC) concept using an ESFC theory. And an equivalent method is then developed with an equivalent growth driving energy concept. A random modeling of the equivalent dominant ESFC growth rates is further constructed for describing the random behaviour of the collective ESFCs nearby the material micro-structure barrier threshold. And the kinetic threshold is subsequently conducted from the modeling. Introduction After Pearson’s work in 1975 to verify that the crack growth law by standard notched specimens can not properly predict the behaviour of the cracks with physical small size in the range of 0.5-1.0 mm [1], the short fatigue crack problem has been focused on all over the world. Two professional meetings had been held respectively at UK [2] and USA [3] in 1986. Since then, short/small crack behaviour has become an important theme of fatigue study. The theme can mainly be subdivided into two fields. One is for a notched specimen or structure with a character of only physical small size crack. Another is for a smooth or blunt specimen or structure with a character of interactive collective micro-cracks. The former has a fatigue damage behavior mainly depending on stress amplitude level and mode. The equivalent stress intensity factor method should be a representative work for well solving the relative engineering structure analysis [4-7]. The later has damage behaviour not only depending stress amplitude level and mode but also the material micro-structures. The damage process was therefore appropriately subdivided into two sequent evolutionary regimes of micro-structural short crack (MSC) and physical short crack (PSC) [8-10], and the fatigue limits should be physically relative to material micro-structural barriers and loading levels [11]. Considering the interactive collective cracks, equilibrium of crack numerical density and equivalent crack size close to the maximum crack size were respectively introduced [12,13]. Distinguishing the fatigue damage difference of the micro-cracks with different orientations and locations and revealing the kinetic evolutionary cracks in a collective and interactive mode, an effective short fatigue crack (ESFC) theory should be previously proposed [14-19]. Railway axle is an important component affecting vehicle’s dynamic behaviour and the transportation safety. The material fatigue properties play a key role for the safety assessment. Consistency with the fatigue damage physics, short crack behaviour is the main damage process. Process work investigates the fatigue threshold on basis of the previous ESFC theory. Material and Experiments Material and Specimens. Smooth axial hourglass shaped specimens of 10 mm diameter (Fig. 1)