拉伸载荷作用下AIN夹杂物对航空用超高强度钢中裂纹萌生的影响

采用扫描电镜原位观测法,跟踪观察了航空用超高强度钢中长方型夹杂物导致裂纹萌生与扩展的微观行为。结果表明,拉伸载荷作用下,航空用超高强度钢中裂纹萌生的方式与夹杂物尺寸及夹杂物周围孔洞的大小有关。当夹杂物面积小于一定值时,无论夹杂物周围有无孔洞,裂纹均以夹杂物／基体界面开裂的方式萌生;当夹杂物面积大于一定值后,若夹杂物／基体界面基本完好,则裂纹易以夹杂物自身开裂的方式萌生;若夹杂物周围孔洞面积较大,则裂纹易以夹杂物／基体界面开裂的方式萌生。     

拉伸载荷作用下AlN夹杂物对航空用超高强度钢中裂纹萌生的影响

 采用扫描电镜原位观测法,跟踪观察了航空用超高强度钢中长方型夹杂物导致裂纹萌生与扩展的微观行为。结果表明,拉伸载荷作用下,航空用超高强度钢中裂纹萌生的方式与夹杂物尺寸及夹杂物周围孔洞的大小有关。当夹杂物面积小于一定值时,无论夹杂物周围有无孔洞,裂纹均以夹杂物/基体界面开裂的方式萌生;当夹杂物面积大于一定值后,若夹杂物/基体界面基本完好,则裂纹易以夹杂物自身开裂的方式萌生;若夹杂物周围孔洞面积较大,则裂纹易以夹杂物/基体界面开裂的方式萌生。     

夹杂物特征参数对拉伸载荷下X80管线钢中裂纹萌生及扩展影响的原位观测

 采用扫描电镜原位观测的方法,跟踪观察了拉伸载荷作用下X80管线钢中不同尺寸、形态的夹杂物导致裂纹萌生与扩展的微观力学行为。结果表明：在拉伸载荷作用下,夹杂物面积越大,夹杂内萌生的裂纹条数越多,第1条裂纹萌生时的应力越小;夹杂物的形态和面积决定第1条裂纹的萌生位置;当夹杂物呈不规则形态且棱角较多时,裂纹在萌生初始阶段就向基体扩展,但之后继续加载时裂纹不会继续在基体中扩展;夹杂物对X80管线钢的拉伸性能无显著影响。     

16Mn钢焊接件疲劳断裂机制研究

对16Mn钢对焊接头的焊缝及热影响区中疲劳裂纹的萌生与扩展机理进行了研究与讨论.结果发现疲裂纹的萌生与扩展与铁素体组织有关,焊接件疲劳断口很复杂,焊缝中的夹杂物对疲劳裂纹的萌生有重要影响.     

夹杂物对超高强度钢应力应变场的影响

非金属夹杂物对钢性能的影响与夹杂物的特征参数密切相关.首先分析拉伸和疲劳载荷下超高强度钢中TiN夹杂物导致裂纹萌生的扫描电镜原位观察结果,采用MSC Marc有限元分析软件对夹杂物及周围基体的应力场进行计算,然后对拉伸载荷下不同特征参数的TiN夹杂物及周围基体的应力应变场进行模拟.结果表明,有限元法能够解释并预测夹杂物及周围基体的力学行为.三角形夹杂物尖角附近的应力集中最严重.矩形夹杂物内部高应力区的位置受夹杂物与外载荷方向夹角的影响.随邻近夹杂物间距的增大,基体内的最大应力由夹杂物外侧移至夹杂物之间.近表面夹杂物使得基体自由表面附近出现高应力区,基体内最大应力的位置受夹杂物与自由表面距离和尺寸的影响.      

82A和82B高强钢疲劳性能的试验研究

对某钢厂生产的82A和82B高强钢进行了高周疲劳性能试验研究,得到了这两种钢的疲劳应力-寿命曲线(S-N曲线)及疲劳强度。用扫描电镜对试样的疲劳断口进行了观察。结果显示,对夹杂物进行变性处理后的82A钢的疲劳裂纹大多从表面缺陷处萌生,而夹杂物没有变性处理的82B钢的疲劳裂纹则从非金属夹杂物及表面缺陷处萌生,且从内部非金属夹杂物处萌生的疲劳断口呈"鱼眼"特征。讨论了非金属夹杂物对高强钢疲劳性能的影响。     

碳钢水平连铸管坯中的夹杂物和内裂纹

本文对水平连铸坯中的主要微观夹杂物——硫化物的数量、分布、形态及与内裂纹之间的关系进行了研究。水平连铸冷凝的特殊过程使得铸坯同一断面上出现不同类型的硫化物夹杂。在拉应力状态下,硫化物(尤其是沿晶分布的Ⅱ型硫化物)易成为裂纹萌生的起源。已形成的裂纹也将沿着硫化物走向扩展。     

航空用超高强度钢中夹杂物导致疲劳裂纹萌生与扩展的微观行为

采用扫描电镜原位观测的方法,跟踪观察了低周疲劳载荷下航空用超高强度钢MA250中夹杂物导致裂纹萌生与扩展的微观行为,得到了MA250钢低周疲劳裂纹萌生与扩展的基本特性,讨论了精确测定MA250钢疲劳裂纹扩展速率的方法.     

高钴钼不锈轴承钢疲劳裂纹萌生及扩展行为

采用高钴钼不锈轴承钢光滑圆柱形试样和缺口试样(理论应力集中系数K_t=3)进行旋转弯曲疲劳测试,研究了高合金轴承钢的裂纹萌生及裂纹扩展行为。用升降法和成组法分别测得轴承钢的疲劳极限和S-N曲线,利用扫描电镜对轴承钢旋转弯曲疲劳试样断口进行观察。结果表明,光滑试样起裂类型为单源萌生起裂,起裂源为表面缺陷和次表面夹杂物,表面缺陷为表面粗糙度、驻留滑移带和加工凹痕,次表面夹杂物为Al_2O_3-CaO-MgO-SiO_2复合夹杂;缺口试样疲劳极限显著下降,起裂类型为多源萌生起裂,计算得轴承钢的缺口敏感系数q_f为1.18。光滑试样疲劳破坏从以高应力幅粗糙度萌生表面裂纹的破坏向低应力幅驻留滑移带、加工凹痕、夹杂缺陷萌生裂纹转移。疲劳裂纹萌生寿命占整个疲劳寿命的94.1%以上。     

汽车排气系统用铁素体不锈钢的耐热性研究

利用实验室条件下冶炼的Fe-Cr-Nb-Mo铁素体不锈钢,对其高温强度和热疲劳性能进行了研究。研究结果表明:实验钢的高温抗拉强度和屈服强度优于或基本相当于目前所使用的铁素体不锈钢的性能;实验钢的热疲劳裂纹从V形缺口处萌生,夹杂物为裂纹萌生优先区域;热疲劳裂纹长度和扩展速度随热疲劳上限温度的升高而增大;热疲劳裂纹优先沿晶界扩展,高温氧化是疲劳裂纹扩展的主要因素。     

A theory of fatigue crack initiation at inclusions

The dislocation dipole accumulation model for fatigue crack initiation previously proposed by the authors is extended to an analysis of the fatigue strength reduction due to inclusions in high strength alloys. The initiation of a fatigue crack is determined by an energy criterion under the assumption that the crack initiation takes place when the self strain energy of dislocation dipoles accumulated at the damaged part in the material reaches a critical value. Explicit formulae for the crack initiation criterion in several cases are derived as functions of the applied stress, the inclusion size, the slip band shape, and the shear moduli of the inclusion and matrix. The following three types of fatigue crack initiation at inclusions are considered: the slip-band crack emanating from a debonded inclusion, the inclusion cracking due to impinging of slip bands, and the slip-band crack emanating from an uncracked inclusion. The first mechanism was reported to be operative in high strength steels, while the last two mechanisms were reported in high strength aluminum alloys. The present theoretical results are in good agreement with the experimental data published for each case of fatigue crack initiation at inclusions.     

The Significance of Crack Initiation Stage in Very High Cycle Fatigue of Steels

Different stages of the Very High Cycle Fatigue (VHCF) crack evolution in tool steels have been explored using a 20 kHz ultrasonic fatigue testing equipment. Extensive experimental data is presented describing VHCF behaviour, strength and crack initiating defects in an AISI H11 tool steel. Striation measurements are used to estimate fatigue crack growth rate, between 10^?8 and 10^?6 m/cycle, and the number of load cycles required for a crack to grow to critical dimensions. The growth of small fatigue cracks within the “fish‐eye” is shown to be distinctively different from the crack propagation behaviour of larger cracks. More importantly, the crack initiation stage is shown to determine the total fatigue life, which emphasizes the inherent difficulty to detect VHCF cracks prior to failure. Several mechanisms for initiation and early crack growth are possible. Some of them are discussed here: crack development by local accumulation of fatigue damage at the inclusion – matrix interface, hydrogen assisted crack growth and crack initiation by decohesion of carbides from the matrix.     

Fatigue Initiation Study of TMT Eutectoid Steel

Eutectoid steel and 1060 steel samples were given a variety of thermomechanical treatments (TMT), described in Table I, which varied the pearlite interlamellar spacing, the cementite and inclusion orientation, the degree of cold-work in the ferrite matrix, and (for 1060 steel only) the proeutectoid grain boundary ferrite network. These samples were then evaluated as to resistance to fatigue crack initiation. The TMT designated, G, involves a subcritical anneal and results in a partially recrystallized condition which shows not only excellent resistance to fatigue crack initiation in the near threshold region but is second only to a fine pearlite microstructure, B, in fatigue crack propagation threshold value. It is believed that the excellent properties of the TMT, G, are related to the formation of subgrains in the interlamellar ferrite. On a scale normalized to tensile strength,(ΔK/√ρ)/σ_u, fine oriented pearlite in a soft ferrite matrix (rapid up-quench TMT such as E, F) shows the best resistance to fatigue crack initiation. A proeutectoid ferrite grain boundary network is poor at resisting fatigue crack initiation but good at resisting fatigue crack propagation. It should be emphasized that the combined high resistance of the subcritical TMT (G) toboth fatigue crack initiation and propagation, coupled with its much easier implementation relative to similar microstructures produced by difficult rapid up-quench TMT's (E, F) make it a very promising approach to improving overall fatigue resistance.     

冶炼工艺对15-5PH不锈钢疲劳性能的影响

 为了研究冶炼工艺对15-5PH不锈钢疲劳性能的影响,通过ASPEX夹杂物分析、拉压疲劳试验和扫描电镜等手段并结合裂纹扩展速率试验,研究了冶炼工艺对15-5PH不锈钢中夹杂物的粒径分布和疲劳性能的影响,并对比了两种试验钢裂纹扩展速率的大小。结果表明,VIM+VAR工艺冶炼的1号试验钢总氧质量分数较低,夹杂物尺寸较小且质量分数较低,1号试验钢的疲劳强度比单真空工艺冶炼的2号试验钢高30 MPa,通过疲劳断口SEM观察,1号试验钢在表面基体起裂,2号试验钢的裂纹源是次表面的Al₂O₃夹杂物;相同条件下,1号试验钢裂纹扩展速率大于2号试验钢。     

A Fatigue Life Model for Predicting Crack Nucleation at Inclusions in Ni-Based Superalloys

Engineering alloys such as Ni-based alloys, Al-alloys, and steels often contain non-metallic inclusions in their microstructures. These inclusions, which include oxide particles, carbides, and intermetallic particles, are introduced during component manufacturing processes such as casting, powder-metallurgy, or additive manufacturing methods. The presence of inclusions in the microstructure can promote fatigue crack nucleation by competing against slipband nucleation and reduce fatigue life performance of an engineering component. While it has been reported in many occasions, the competition between fatigue crack nucleation at inclusions and slipbands is still not well understood. In this article, the conditions for the concurrent occurrence of fatigue crack nucleation at inclusions and slipbands are analyzed theoretically. The analysis indicates that there exists a critical inclusion size (diameter) below which there is no fatigue life debit due to crack initiation at inclusions and above which a transition from slip-induced to inclusion-induced crack nucleation occurs. The low-cycle fatigue life model is applied to Ni-based superalloys and the model predictions are compared against experimental data from the literature to assess the dependence of the critical inclusion size on the slip morphology, grain size of the matrix, and the shear modulus of the inclusion.     

Environmentally Influenced Mixed Mode Fatigue Crack Propagation of Titanium Metal Matrix Composites

Effect of humid air environments on the mixed mode fatigue crack propagation behavior of B₄C-B and BORSIC reinforced Ti-6A1-4V metal matrix composites was studied. Humid environments enhanced the mixed mode fatigue crack propagation rates in the as-received titanium matrix composites atR = 0.1. The effect was more pronounced in the transverse and 45 deg specimens. A transition in failure modes from fiber splitting in humid air to interfacial splitting in dry environments was observed at a load ratio of 0.1. The transition took place at around 100 Pa water vapor pressure, where a steep rise in fatigue crack propagation rate was noticed. AtR = 0.5, however, no fiber splitting was observed in humid air. Fatigue crack closure load measurements revealed that closure loads were higher in humid air than in dry environments. The fiber splitting is suggested as an environmentally induced crack closure effect, where plastically deformed matrix sets up stress fields (radial and mode III stresses) on the brittle boron fibers weakened by the humidity.     

Initiation of fatigue cracks in 4340 steel

Electron microscopy of surface replicas has been employed to determine the metallurgical micromechanics of fatigue crack initiation at surface and shallow subsurface inclusions in 4340 steel. The experimental results are considered in terms of current theoretical analyses of elastic stress distributions around hard inclusions imbedded in soft matrices. A model for crack nucleation at surface inclusions is suggested, based upon debonding of the inclusion/matrix interface at the tensile pole of the inclusion, followed by growth of the debond seam toward the inclusion “equator”. Subsequent generation of a matrix crack is associated with the initiation of “point” surface defects some distance from the inclusion/matrix boundary, but in the plane of the inclusion “equator”. Surface slip plays no discernible role in nucleation of surface inclusions, but slip bands are formed at crack sites above sub-surface inclusions. However, the microcracks continue to form through the link-up of point surface defects.     

Effect of SiC volume fraction and particle size on the fatigue resistance of a 2080 Al/SiC p composite

The effect of SiC volume fraction and particle size on the fatigue behavior of 2080 Al was investigated. Matrix microstructure in the composite and the unreinforced alloy was held relatively constant by the introduction of a deformation stage prior to aging. It was found that increasing volume fraction and decreasing particle size resulted in an increase in fatigue resistance. Mechanisms responsible for this behavior are described in terms of load transfer from the matrix to the high stiffness reinforcement, increasing obstacles for dislocation motion in the form of S’ precipitates, and the decrease in strain localization with decreasing reinforcement interparticle spacing as a result of reduced particle size. Microplasticity was also observed in the composite, in the form of stress-strain hysteresis loops, and is related to stress concentrations at the poles of the reinforcement. Finally, intermetallic inclusions in the matrix acted as fatigue crack initiation sites. The effect of inclusion size and location on fatigue life of the composites is discussed.     

Fatigue crack initiation and propagation behavior of high cobalt molybdenum stainless bearing steel

The crack initiation and propagation behavior of high cobalt molybdenum stainless bearing steel was studied by rotating bending fatigue test with smooth cylindrical specimens and notched specimens (theoretical stress concentration factor Kt=3). The fatigue limit and S- N curve of bearing steel were measured by up- and- down method and group method, respectively. The fractures of the specimens were observed by scanning electron microscopy. The results show that the cracking type of the smooth specimens is single source initiation. The crack source is surface defects and subsurface inclusion. The surface defects are surface roughness, persistent slip band and machining dent, while the subsurface inclusion is Al2O3- CaO- MgO- SiO2 composite inclusion. The fatigue limit of notched specimens is significantly decreased. The cracking type of the notched specimens is multi- source initiation. The notch sensitivity factor qf of bearing steel is 1. 18. The fatigue failure of the smooth specimens is transferred from the surface roughness with high stress amplitude to the persistent slip bands, the machining dents and the inclusions with low stress amplitude. The fatigue crack initiation life accounts for more than 94. 1% of the whole fatigue life.     

Exoelectron emission from torsional fatigue damage in hardened steels

Exoelectron emission associated with surface fatigue damage in two types of steel was measured by means of an ultraviolet laser scanning system. The localized emission from damage areas in quenched and tempered 1541 steel increased systematically with continued fatigue cycling. Plots of emissionvs cycles were in good agreement with earlier results for 1018 steel. Much of this emission resulted from the accumulation of plastic deformation during the crack initiation stage. In the case of relatively brittle 1144 steel, the dominant source of exoelectrons was a fatigue crack with little associated plasticity. However, shot peening of the 1144 steels completely changed the character of the surface layers. While the core material still cracked in a rather brittle manner, the shot peened layer accumulated a broad distribution of plastic deformation as revealed by the systematic development of exoelectron emission. These results indicate that the accumulation of surface fatigue deformation during the crack initiation stage is a systematic and perhaps universal process when viewed on the appropriate microscale.