13SiMNiCrMov钢切口疲劳裂纹萌生门槛值

本文研究在１３ＳｉＭｎＮｉＣｒＭｏＶ结构钢中用尖裂纹的应力强度因子来反映三点弯曲缺口试样的疲劳裂纹萌生规律。当Ｒ＝０．１ｆ＝１００Ｈｚ，试样尺寸Ｂ＊Ｗ＊Ｌ＝１２．５＊２５＊１１７ｍｍ时，缺口名义应力幅的门槛值为△σｔｈ＝３３１５ρ＾０．３５２ＭＰａ，０．５ｍｍ≤ρ≤５ｍｍ，△Ｋｔｈ＝２５０ρ０．３５２ＭＰａｍ门槛值与ρ有关。同时得到缺口裂纹萌生的循环次数Ｎｉ与名义应力幅△σ，缺口曲率半径ρ的定量关     

疲劳裂纹扩展门坎值的预测

根据裂纹尖端范性钝化临界条件的分析和应力比R对金属疲劳裂纹扩展的影响,得出计算应力强度因子范围门坎值的一般公式: △K_(th)=Eε_f((2πρ_(min))~(1/2))(1—R)~γ 式中ρ_(min)为柏氏矢量的绝对值,|B|,由上式得到的计算值与实验结果是基本相符的。     

受阴极保护的低碳钢的腐蚀疲劳裂纹扩展

利用测定疲劳裂纹增长速率的方法研究了在天然海水中阴极保护对低碳钢腐蚀疲劳裂纹增长性状的影响。假设临界应力强度因子幅值△K_(th)相当于(1～2)×10~(■)毫米/周的裂纹增长速率时的应力强度因子幅值,则在空气中△K_(th)为3.9兆牛顿/米~3/~2,在海水中为2.3牛顿/米~3/~2,而在海水中阴极极化(-800毫伏、相对 S.C.E)条件下为5.4兆牛顿/米~3/~2。应力强度因子幅值和裂纹增长速率之间关系在空气中增长速率为3×10~(-7)～2×10~(?)毫米/周和在海水中-800毫伏(相对 S.C.E)以及在海水中增长速率为1×10~(-7)～1×10_■毫米/周的情况下遵守 Paris 规律。发现在海水中的裂纹增长速率的最高值比在空气中的快两倍,但在海水中-800毫伏(S.C.E)条件下,其裂纹增长速率降低到约为在空气中裂纹增长速率范围内的40%。利用扫描电镜研究了试样腐蚀疲劳裂纹表面的断口组织。发现在海水中阴极极化的试样裂纹表面上形成钙质沉积物。在海水中阴极保护的试样出现腐蚀疲劳裂纹增长的终止现象可以解释为:由裂纹中海水生成的阴极反应钙质产物的楔入作用。     

TA5钛合金冲击断裂时的裂纹扩展特征

TA5钛合金板材,经840℃退火处理,加工成10×10×55(mm)的夏比V型缺口试样和预制疲劳裂纹试样,用示波冲击试验方法,求得最大裂纹扩展速率da/dt为9.15m/s;平均速率da/dt为6.44m/s;动态断裂韧性K_(1d)为55.4MPam~1/~2。     

NdBO_3和 Nd(BO_2)_3的标准生成自由能

用 CaF_2单晶和 ZrO_2(+MgO)为固体电解质分别构成原电池:■和 Pt,B_((s)),NdBO_(3(s)),Nd(BO_2)_(3(s))|ZrO_2|Cr_2O_(3(s)),Cr_((s)),Pt联合测了 NdBO_3和 Nd(BO_2)_3的标准生成自由能:ΔG~0_(NdBO_3)=-1757+3.8×10~(-1)TΔG~0_(Nd)(BO_2)_3=-3435+8.8×10~(-1)T由此求出由氧化物生成 NdBO_3及 Nd((BO_2)_3)的反应的标准生成自由能变化:1/2Nd_2O_(3(s))+1/2B_2O_(3■)=NdBO_(3(s))ΔG~0_(NdBO_3)=-242+1.4×10~(-1)T和 1/2Nd_2O_(3(s))+3/2B_2O_(3(s))=Nd(BO_2)_(3■)ΔG~0′_(NdBO_2)3=-693+4.6×10~(-1)T     

LY-12CS铝合金在空气和盐水介质中△K_(th)和da/dN规律的研究

本文用中心缺口拉伸试样(CCT试样)测试了LY-12CS铝合金在室温空气和3.5％NaCl水溶液介质中三种载荷比(R=0,R=0.33,R=0.67)条件下的疲劳裂纹扩展门坎值△K_(th)及da/dN,结果表明: (1)在三种载荷比条件下,盐水介质比空气介质明显地降低了△K_(th)而提高了疲劳裂纹扩展速率da/dN。在我们试验的三种载荷比△K=7～15kg/mm~(3/2)范围内,盐水介质的da/dN是空气介质的1.6～3.4倍。 (2)在两种介质中,随着载荷比R(或平均应力)的增加,门坎值△K_(th)下降而da/dN增加。     

金属疲劳裂纹初期扩展的特征及其影响因素

本文回顾了各种金属及合金在门坎区附近的疲劳裂纹扩展的机制和特徵。 根据一系列试样和结构的微观断口金相分析的结果表明,在近门坎区产生的占主导的断口形态是小平面或河流花样。对于不同金属与合金小平面的方位与晶体点阵结构的相互关系,用滑移型和层错能进行描述,在非轴向载荷下,曾提出一个更为普遍的疲劳裂纹扩展特性。 在本文中,对于板状及缺口试样的疲劳极限和门坎值的相互关系以及短裂纹的疲劳裂纹扩展机制也一起进行了评述,短裂纹的裂纹扩展行为可以一般地表达为: △K_(th)=f(a)△σ_(th)(πa)~(1/2)式中,f(a)为裂纹长度与试样几何形状的函数。 本文对应力比、显微组织、环境对在门坎区附近疲劳裂纹扩展行为的影响也进行了回顾,曾提出产生裂纹闭合效应的“氧化物诱发”及“粗糙度诱发”的概念,可以用来解释结构材料中上述因素对在近门坎区疲劳裂纹扩展行为的影响。     

弹性铜合金带的弯曲疲劳试验

自行设计,制造了带材弯曲疲劳试验机。采用恒应力试样,对国产厚度为0.4mm 为铍青铜(QBe2固溶处理后,320℃3h 时效)和锡磷青铜(QSn6.5～0.1硬态)进行了弯曲疲劳试验,得出了它们的疲劳极限为,铍青铜σ_(-1)(10~7)=S45N/(mm)~2,锡磷青铜σ_(-1)(5×10~6)=154N/(mm)~2,与国外同类材料相比,锡磷青铜疲劳极限至少要低40%左右。对疲劳后的断口进行了观察。     

TB6钛合金疲劳小裂纹扩展行为

为了研究TB6钛合金自然萌生小裂纹的扩展行为,针对单边缺口拉伸试样开展室温下不同应力比(R=0.1,0.5)的小裂纹扩展实验,采用复型法观测了小裂纹的萌生与扩展情况。结果表明:同一应力比下,随着应力等级的降低,小裂纹的萌生寿命由占全寿命的60%增加到80%,但应力等级对TB6钛合金小裂纹扩展速率没有明显影响。裂纹早期扩展速率受微观组织的影响大,TB6钛合金扩展速率转变临界值是200μm,一旦裂纹长度达到200μm,裂纹扩展速率将不受取向不同的晶界或晶粒影响而迅速提升。TB6钛合金疲劳小裂纹起源于试样缺口根部,所有试样的裂纹大部分为角裂纹,疲劳小裂纹萌生寿命占全寿命的绝大部分。     

挤压SiCw／LD2复合材料的疲劳裂纹扩展

本文测量了挤压19％(Vol)SiCw/LD2复合材料疲劳裂纹扩展的门槛值ΔK_(th)和扩展速率da/dN。并在扫描电镜下观察了疲劳断口形貌。结果表明,复合材料在门槛值附近和中速扩展区的疲劳裂纹扩展抗力高于基体材料LD2合金。复合材料纵向试样于170℃时效后的疲劳裂纹扩展抗力高于150℃时效,疲劳裂纹扩展扩展过程包括不在一个面内的微裂纹长大和联接这些微裂纹的(Ⅰ+Ⅱ)复合型裂纹的扩展。与裂纹相垂直的晶须有效地阻碍了微裂纹的长大。     

A THERMAL SHOCK FATIGUE STUDY OF TYPE 304 AND 316 STAINLESS STEELS

–Thermal fatigue crack initiation and propagation promoted by thermal quenches have been studied in AISI 316 and 304 stainless steels and correlated with isothermal strain cycling fatigue. Axially unconstrained specimens of rectangular section were held at bulk temperatures of 250°C to 500°C and symmetrically water-quenched on the narrow faces to give equivalent surface strain ranges from 2.8 ×10^?3 to 5.4 ×10^?3. Crack initiation in smooth samples showed an apparent threshold at a surface strain range of 2.8×10^?3 equivalent to a thermal amplitude of 150°C with no cracking being produced in 500,000 cycles. The crack growth in prenotched samples was evaluated by direct observation and by subsequent fractography and showed two modes of growth. The crack growth was strain controlled during the early stages of propagation where the crack tip was within the surface zone under conditions of fully plastic cyclic yield. At greater depths the propagation rates in the remaining elastically cycled material were found to correlate with calculated stress intensity values. In the chosen symmetrical quenched axially unconstrained configuration the crack growth rates decreased towards the centre of the specimen, indicating a crack arrest condition as expected from analysis. The results indicated a good correlation with the fracture behaviour observed from isothermal strain cycling fatigue behaviour in an air environment.     

INITIATION AND GROWTH OF SMALL CRACKS IN DIRECTIONALLY SOLIDIFIED MAR-M247 UNDER CREEP-FATIGUE PART II: EFFECT OF ANGLE NETWEEN STRESS AXIS AND SOLIDIFICATION DIRECTION

This paper deals with the effect of anisotropy on fracture processes of a directionally solidified superalloy, Mar-M247, under a push–pull creep-fatigue condition at high-temperature. Three kinds of specimen were cut from a cast plate such that their axes possess angles of 0°, 45° and 90° with respect to the 〈001〉 orientation that is aligned parallel to the solidification direction (also to the grain boundaries and primary dendrite axis); these specimens being denoted the 0° specimen, the 45° specimen, and the 90° specimen, respectively. The tests were conducted at 1273  K (1000 °C) in air under equal magnitudes of the range of a Δ J -related parameter, Δ W _c , which represents the driving force for crack growth in creep-fatigue. Although the grain boundaries are macroscopically parallel to the solidification direction, they are wavy or serrated microscopically. Small cracks nucleate along parts of the grain boundaries perpendicular to the stress axis in all specimens. The 90° specimen has the shortest crack initiation life and the 0° specimen has the longest. In the 90° and 45° specimens, intergranular cracks continue to nucleate and a main crack is formed along the grain boundary due to the frequent coalescence of small cracks. In the 0° specimen, cracks grow into the grain, and transgranular cracks coalesce along the primary dendrite or grain boundary. The 0° specimen exhibits the slowest crack growth rate and the 90° specimen the fastest. These differences in the initiation and growth behaviour of small cracks cause the longest failure life in the 0° specimen and the shortest in the 90° specimen.     

Mixed-mode crack growth in ductile thin-sheet materials under combined in-plane and out-of-plane loading

Ductile thin-sheet structures, such as fuselage skin or automobile panels, are widely used in engineering applications. These structures often-times are subjected to mixed mode (I/II/III) loading, with stable crack growth observed prior to final fracture. To characterize specific specimen deformations during stable tearing, a series of mixed-mode I/III stable tearing experiments with highly ductile thin-sheet aluminum alloy and steel specimens have been measured by using three-dimensional digital image correlation (3D-DIC). Measurements include (a) specimen’s deformed shape and 3D full-field surface displacement fields, (b) load-crack extension response and (c) crack path during stable tearing, (d) angular and radial distributions of strains and (e) the mixed mode crack-opening displacement (COD, measured at 1-mm from crack tip along crack surface) variation as a function of crack extension. Results indicate that for both aluminum alloy and steel at all mixed-mode I/III loading conditions (Φ = 30°, 60° and 90°), the crack tip fields have almost identical angular and radial polar strain distributions. The mixed mode I/III fields were different from those observed for the nominal Mode I loading case (Φ = 0°). The effect of the Mode III loading component is that it lowers the magnitude of the dominant strain component ε _θθ ahead of the growing crack tip and increases the singularity of the strain as compared with that in the mode I case. In addition, measurements indicate that the average mixed mode I/III stable COD for AL6061-T6 (GM6208 steel) is 4×(3×) greater than the average Mode I stable COD.     

Effect of crack curvature on stress intensity factors for ASTM standard compact tension specimens

The stress intensity factors (SIF) are calculated using the method of lines for the compact tension specimen in tensile and shear loading for curved crack fronts. For the purely elastic case, it was found that as the crack front curvature increases, the SIF value at the center of the specimen decreases while increasing at the surface. For higher values of crack front curvatures, the maximum value of the SIF occurs at an interior point located adjacent to the surface. A thickness average SIF was computed for parabolically applied shear loading. It is assumed that it reflects the average stress environment near the crack edge. These results were used to assess the requirements of ASTM standards E399-71 and E399-81 on the shape of crack fronts.     

THE INFLUENCE OF SPECIMEN GEOMETRY ON NEAR THRESHOLD FATIGUE CRACK GROWTH

Abstract— The near threshold fatigue behavior of a nickel base superalloy and a wrought 2024 aluminum alloy is examined as a function of specimen geometry. Experimental results revealed that for a given value of Δ K in Region I, crack growth rates were observed to increase as the specimen loading became more symmetric with respect to the load line. Compact tension type specimens exhibited lower crack growth rates than the more symmetrically loaded center cracked tension specimens. Consideration of the observed discrepancies is given in terms of the near field crack tip stress distribution and deformation behavior of the material affecting crack advance.     

COMPARISON OF PLASTIC WORK OF FATIGUE CRACK PROPAGATION IN LOW CARBON STEEL MEASURED BY STRAIN-GAGES AND ELECTRON CHANNELING

Abstract— The plastic work to propagate a fatigue crack by a unit area, U, measured by the foil strain gage technique requires an extrapolation to estimate the contribution closer than 100 μm to the crack tip. This is due to the size of the strain-gages used, 200 × 210 μm. Conversely, the electron channeling technique for determining U is useful mainly close to the crack tip where subgrains form. In the present work U was measured by both techniques in the same low carbon steel at ΔK= 8 MN/m^3/2. The contribution to U from closer than 100 μm of the crack tip was determined to be 1·7 × 10⁶ J/m² using electron channeling and 2·0 × 10⁶ J/m² by extrapolation. The measured contribution to U from further than 100 μm from the crack tip was 3·6 × 10⁶ J/m² giving 5·3 × 10⁶ J/m² for U. Thus, a large amount of energy is absorbed outside the region where sub-grains form. The non-hysteretic plastic work was found to be about four orders of magnitude smaller than the hysteretic plastic work, and may be neglected. A map of the plastic zone results from the strain-gage measurement. Rice's theory predicts the measured plastic zone sizeif the proper material's strength is employed in the formula.     

A monitoring system for contact fatigue crack testing

A new monitoring system is developed to detect crack initiation and propagation in the surface layer during contact fatigue running. The magnetic head of a commercial tape recorder is used as a probe. A combination of leakage and eddy current methods is ussed for the contact roller specimen on the JPM-1 machine. Experimental results show that this system is very sensitive to artificial defects and can distinguish defects on the surface from those beneath the surface. The defect signals agree well with their positions. Testing of an ion-nitrided specimen shows that a tiny subsurface crack (∼ 1 μm), which can only be examined under a microscope with 200 × magnification, is observable with this system.     

A MODEL OF FATIGUE CRACK GROWTH AFTER AN OVERLOAD IN D16T Al-ALLOY SUBJECTED TO BIAXIAL CYCLIC LOADS AT VARIOUS R-RATIOS

Abstract— Fatigue crack growth after a biaxial overload has been investigated. The crack retardation parameters, N _D, and, a _D, do not have monotonous dependencies on the biaxial stress ratio, λ, because the shear stress, τ_III, acting in the perpendicular direction of the specimen face, influenced the values of these parameters.
It has been found that the plastic zone size parameters, r _ab, and Δ, do not increase monotonously with increasing λ ratio. The plastic zone size in the crack growth direction, r _ho= a _D13, was calculated on the basis of newly proposed relations.
Crack growth after an overload was simulated on the basis of the equivalent mode I stress intensity factor, IC_C, invoking a unified kinetic diagram and calculated crack increments, a _D13 and a _D=Δ_c, where Δ_c is the maximum value of the calculated size of plastic zone. The experimental data for crack growth after an overload had good agreement with the calculated data.     

The measurement of fatigue cracks at spot-welds

Current fabrication changes in the automotive industry have stimulated interest in fatigue avoidance at spot-welded joints. Basic endurance data are available only for specific specimen types; a generalized fracture mechanics approach has been impeded by lack of crack propagation data. This paper describes a direct current potential difference technique for the continuous measurement of crack dimensions in spot-welded mild steel specimens under fatigue loadings. Initial results indicate that macrocrack propagation is the dominant fatigue mechanism for specimens with lives of the order 2 × 10⁶ cycles.     

EFFECT OF FATIGUE CRACK CLOSURE ON NEAR-THRESHOLD CRACK RESISTANCE OF STRUCTURAL STEELS

Abstract— The present paper is an attempt to clarify conditions for plasticity-induced and oxide-induced crack closure as well as to evaluate the effect of crack closure on near-threshold fatigue crack behaviour.
The autocatalytic character of oxide formation at the crack tip has been elucidated in this study. An increase of plastic constraint at the crack tip is shown to intensify the fretting oxide formation process on the fracture surface and thus to cause an increase of the stress intensity factor range controlling the fatigue crack propagation rate. The proposed concept of stress state influence on crack closure allows us to explain the effect of specimen thickness on Δ K _th.