Fatigue crack growth behavior of a solid solution-strengthened nickel-base superalloy (Incoloy 825)

Fatigue crack growth behavior of a solid solution-strengthened nickel-base superalloy (Incoloy 825)* was investigated. The investigation also examined the influence of heat treatment on resultant microstructures and the near-threshold fatigue crack growth behavior. In addition, the influence of load ratios(R), material strength, and grain size on fatigue threshold was studied. Compact tension specimens prepared from Incoloy 825 with transverse-longitudinal (TL) orientation in the as-received, as well as two different heat treated conditions, were used. The heat treatment studies revealed a peak hardness condition after solution treatment at 1200 °C for 1/2 hr, followed by aging at 600 °C for 434 hr. Among all the heat treated conditions, the fatigue threshold was the highest and the near-threshold crack growth rate was lowest in this peak aged condition. Fatigue threshold values were observed to decrease with an increase in load ratio, whereas an increased grain diameter resulted in a higher fatigue threshold. An earlier mathematical model was found applicable to characterize the relationship between load ratio and fatigue threshold. Preferential etching of grain boundary suggests formation of a thin film of carbide precipitation along the grain boundary region in the aged specimens. This carbide precipitation facilitated intergranular crack growth in these samples, resulting in higher roughness-induced crack closure. The highest fatigue threshold in the peak aged condition can be attributed to this large roughness-induced crack closure process. Incoloy 825 is a trademark for products of Huntington Alloys, Inc.     

Effect of boron and carbon on the fracture toughness of IN 718 superalloy at room temperature and 650 °C

The effect of B and C microadditions on the fracture toughness of IN 718 superalloy was investigated at room temperature (RT) and at 650 °C. At RT, the fracture toughness was observed to increase with increasing B and C concentrations. C had a relatively weak effect on the fracture toughness at 650 °C, but the influence of B was significant. At RT the highest fracture toughness value was obtained for the alloy with 29 ppm B and 225 ppm C at RT, and at 650 °C the alloy with 60 ppm B and 40 ppm C had the highest fracture toughness. An increase in the concentration of B to 100 ppm, however, resulted in a reduction in the fracture toughness at 650 °C. Fractographic observations showed that the formation and coalescence of microvoids was the predominant fracture mechanism at RT. In contrast, at 650 °C, the fracture surface exhibited intergranular cracking in the alloy with lower B concentrations and transgranular cracking coupled with fine dimples in the alloy with higher B concentrations. It is suggested that B impedes intergranular cracking by increasing the cohesion of grain boundaries and improving the grain boundary stabilization. The RT increase in the fracture toughness of the material caused by the addition of C is attributed to the formation of intergranular and intragranular carbides that increased the resistance to the plastic deformation.     

Investigation of Mechanical Properties and Fracture Simulation of Solution-Treated AA 5754

In this work, mechanical properties and fracture toughness of as-received and solution-treated aluminum alloy 5754 (AA 5754) are experimentally evaluated. Solution heat treatment of the alloy is performed at 530 °C for 2 h, and then, quenching is done in water. Yield strength, ultimate tensile strength, impact toughness, hardness, fatigue life, brittle fracture toughness \((K_{\text{Ic}} )\) and ductile fracture toughness \((J_{\text{Ic}} )\) are evaluated for as-received and solution-treated alloy. Extended finite element method has been used for the simulation of tensile and fracture behavior of material. Heaviside function and asymptotic crack tip enrichment functions are used for modelling of the crack in the geometry. Ramberg-Osgood material model coupled with fracture energy is used to simulate the crack propagation. Fracture surfaces obtained from various mechanical tests are characterized by scanning electron microscopy.     

Structure and fracture of granulated alloy ÉP741NP after fatigue tests

The structure and properties of high-alloy refractory nickel alloy ÉP741NP after quenching and aging in a standard mode with additional heating to 650°C (τ = 4 h), 870°C (τ = 10 h), and 1000–1050°C (τ = 2.5 h) that corresponds to operating conditions and production processes of specific parts are studied. The rate of growth of fatigue cracks is determined as a function of the amplitude of the stress intensity factor at 20 and 650°C. Data on the types of fracture surface textures for fatigue crack propagation and various values of this factor are obtained.     

Fatigue crack growth behavior of laser-processed 304 stainless steel in air and gaseous hydrogen

Fatigue crack growth test was performed to evaluate fatigue behavior of 304 stainless steel specimens with or without laser processing (welding and surface treatment) in air and gaseous hydrogen. As the crack propagation normal to the laser welding or scan direction, the laser-processed specimens exhibited a higher resistance to crack growth in the low stress intensity factor range (ΔK) than the as-received steel plates regardless of testing environments. However, the marked retardation of crack growth behavior vanished for welded specimens subjected to a 850 °C/h stress relief treatment or with a shorter distance from notch tip to the weld centerline in the test.Fatigue-fractured appearance of the steel plate tested in air was composed of mainly transgranular fatigue fracture and some flat facets, along with a small amount of intergranular fracture. While quasi-cleavage fracture and few twin boundary separations were observed for the same specimen in hydrogen. On the other hand, the lower crack growth rate of laser-processed specimens in both air and hydrogen was accompanied with rubbed areas on the fracture surfaces. It was found that the extent of quasi-cleavage fracture was related to the formation of strain-induced martensite, which would contribute to an increased fatigue crack growth rate of all specimens in gaseous hydrogen.     

Effect of cooling rate on microstructure and tensile properties of powder metallurgy Ni-based superalloy

The effects of size distribution, morphology and volume fraction of γ′ phase and grain size on tensile properties of powder processed Ni-based superalloy were investigated by using two different quenching methods. Oil quenching and air cooling were adopted with cooling rate of 183 °C/s and 4–15 °C/s, respectively. The experimental results show that the average size of the secondary γ′ after oil quenching is 24.5 nm compared with 49.8 nm under air cooling, and corresponding volume fractions of γ′ are 29% and 34%, respectively. Meanwhile, the average grain size remains nearly equivalent from both oil-quenching and air-cooling specimens. The tensile strength at room temperature is higher for the oil-quenched specimen than the equivalent from the air-cooled specimen, but the difference approaches each other as the temperature increases to 650 °C. The fractography clearly demonstrates that transgranular fracture governs the failure process at ambient temperature, in contrast to the intergranular fracture at 650 °C or even higher temperature. These two mechanical responses indicate the strengthening effects of γ′ precipitates and grain boundary for polycrystalline Ni-based superalloys at different temperatures.     

Specific Features of the Nucleation and Growth of Fatigue Cracks in Steel under Cyclic Dynamic Compression

The processes of the fracture of 40Kh and U8 steels under cyclic dynamic compression are studied. It has been found that the main cause for the fracture of the cyclically compressed specimens is the propagation of cracks due to the effect of residual tensile stresses, which arise near the tips of the cracks at the stage of the unloading of the specimens. The growth rate of a crack has the maximum value at the initial stage of its propagation in the vicinity of the stress concentrator. As the crack propagates deep into the specimen, its growth rate decreases and depends only slightly on the real cross section of the specimen. The model of the process of the fatigue fracture of the steels under dynamic loading by a cyclically varied compressive force is proposed. It has been found that the high fatigue endurance is provided by tempering at 200°C for the 40Kh steel and at 300°C for the U8 steel.     

Aging precipitation behavior and its influence on mechanical properties of Mn18Cr18N austenitic stainless steel

The aging precipitation behavior in Mn18Cr18N austenitic stainless steel was investigated at temperatures from 600 °C to 900 °C. During isothermal aging treatment, the primary precipitate was Cr₂N with a = 0.478 nm and c = 0.444 nm, and it preferentially nucleates along initial grain boundaries and gradually grows towards the interior of grains in discontinuous cellular way. Meanwhile, a small amount of granular face-centred cubic M₂₃C₆ with a = 1.066 nm also were observed, which mainly form along grain boundaries. The effect of these precipitates on mechanical properties of the alloy was studied. It was found that precipitates result in degeneration of the matrix hardness. Meanwhile, the SEM morphologies of aged tensile sample show that the brittle fracture predominates during deformation, i.e. the fracture mode transforms from intergranular fracture to transgranular fracture with the increasing of aging time. Compared with the solution-treated sample, the strength of the aged tensile samples slightly decreases and plasticity remarkably deteriorates.     

The effect of annealing on microstructure and tensile properties of Ti–22Al–25Nb electron beam weld joint

This study investigated the microstructure evolution and tensile properties of Ti–22Al–25Nb EBW joints. The fusion zone of the as-welded joint exhibited a fully B₂ microstructure. Widmanstätten O particles precipitated out of B₂ matrix after annealing and their size increased within a temperature range from 750 °C to 900 °C. In the heat affected zone, there was a transition of microstructure moving away from the fusion zone towards the base material. Strength and elongation of the as-welded sample were significantly improved after annealing, which was attributed to the strengthening effect of O precipitates and the slip transmission between O and B₂ phases. Samples tensile tested at 650 °C all failed within the fusion zone and exhibited intergranular failure instead of transgranular failure at room temperature. The room temperature strength and hardness of the joints decreased with annealing temperature due to the coarsening of O precipitates. At 650 °C, failure occurred by intergranular fracture in the fusion zone and the joint strength of all annealed samples was similar due to similar B₂ grain boundary strength.     

The effect of sensitization on the hydrogen-enhanced fatigue crack growth of two austenitic stainless steels

Fatigue crack growth tests were performed to evaluate the susceptibility to hydrogen-enhanced crack growth of AISI 304 and 316 stainless steels (SSs). Sensitization treatment at 650 °C 100 h played little effect on the fatigue crack growth behavior in air, regardless of testing specimens. However, hydrogen accelerated the fatigue crack growth of various specimens to different degrees; sensitized specimens were more susceptible as compared with the un-sensitized ones.

Fatigue fracture appearance of various specimens tested in air exhibited mainly transgranular fatigue fracture together with rarely intergranular fracture and twin boundary separation. Meanwhile, intergranular fracture was found for sensitized specimens tested in hydrogen. Extensive quasi-cleavage fracture related to the strain-induced martensite accounted for the hydrogen-accelerated fatigue crack growth of unstable austenitic SSs. On the other hand, the lower susceptibility of 316H specimens could be attributed to the partial austenite transformation, as evidenced by a mixture of transgranular fracture feature and quasi-cleavage.     

Role of the grain-boundary phase on the elevated-temperature strength,toughness, fatigue and creep resistance of silicon carbide sintered with Al,B and C

The high-temperature mechanical properties, specifically strength, fracture toughness, cyclic fatigue-crack growth and creep behavior, of an in situ toughened silicon carbide, with Al, B and C sintering additives (ABC-SiC), have been examined at temperatures from ambient to 1500°C with the objective of characterizing the role of the grain-boundary film/phase. It was found that the high strength, cyclic fatigue resistance and particularly the fracture toughness displayed by ABC-SiC at ambient temperatures was not severely compromised at elevated temperatures; indeed, the fatigue-crack growth properties up to 1300°C were essentially identical to those at 25°C, whereas resistance to creep deformation was superior to published results on silicon nitride ceramics. Mechanistically, the damage and shielding mechanisms governing cyclic fatigue-crack advance were essentially unchanged between ∼25°C and 1300°C, involving a mutual competition between intergranular cracking ahead of the crack tip and interlocking grain bridging in the crack wake. Moreover, creep deformation was not apparent below ∼1400°C, and involved grain-boundary sliding accommodated by diffusion along the interfaces between the grain-boundary film and SiC grains, with little evidence of cavitation. Such unusually good high-temperature properties in ABC-SiC are attributed to crystallization of the grain-boundary amorphous phase, which can occur either in situ, due to the prolonged thermal exposure associated with high-temperature fatigue and creep tests, or by prior heat treatment. Moreover, the presence of the crystallized grain-boundary phase did not degrade subsequent ambient-temperature mechanical properties; in fact, the strength, toughness and fatigue properties at 25°C were increased slightly.     

7050高强铝合金铆钉丝材T73双级时效工艺

针对国产7050高强铝合金铆钉丝材,采用室温拉伸、室温剪切、镦粗试验的方法,研究了经177～182℃不同二级时效时间后7050铝合金丝材的性能。利用扫描电镜(SEM)、透射电镜(TEM)观察合金不同时效工艺下断口组织和析出相形貌特征。结果表明,拉伸强度和剪切强度随二级时效温度的升高、二级时效时间的延长逐渐降低,剪切强度低于330 MPa时镦粗试样不开裂。TEM微观组织显示,随二级时效温度的升高、时间的延长析出相形貌变化不大,但析出相的尺寸随时效温度的升高逐渐长大、间距逐渐增大;拉伸断口形貌显示,二级时效的断裂方式均为韧窝断裂和沿晶断裂的混合断裂模式,随二级时效温度的升高和保温时间的延长,断口中韧窝数量逐渐增加且尺寸变大,沿晶断裂逐渐减少。     

低成本β钛合金热处理后的显微组织变化和力学性能(英文)

研究了时效时间对低成本β(LCB)Ti-6.6Mo-4.5Fe-1.5Al钛合金的显微组织和力学性能的影响,以及显微组织与疲劳断裂裂纹的产生、延伸的联系。延长时效时间有助于二次α相和β晶粒体积分数的增多以及初始α相的部分球化。在500°C下热处理0.5h的合金得到的拉伸强度最大(1565MPa),疲劳极限最高(750MPa);而在500°C下热处理4h的合金得到的拉伸强度最小(1515MPa),疲劳极限最低(625MPa)。在500°C下热处理4h的合金的断裂模式为穿晶断裂,而在500°C下热处理0.5h的合金的断裂模式为穿晶断裂和沿晶断裂的混合。在疲劳样品的外表面形成的裂纹沿β晶界上初始α相延伸。     

不同温度时效后17-4PH不锈钢的高周腐蚀疲劳性能

对17-4PH不锈钢进行固溶+稳定化+时效处理,分析了568 ℃和605 ℃两种温度时效后17-4PH不锈钢的显微组织、硬度、裂纹扩展速率、腐蚀疲劳断口以及疲劳极限。结果表明:时效温度为568 ℃的17-4PH不锈钢疲劳极限相对于605 ℃时效温度的疲劳极限明显提高,其疲劳裂纹扩展门槛值高于605 ℃的,疲劳扩展速率明显低于605 ℃的。两种温度时效后钢的疲劳断口均属于解理断裂。     

Design of multistep aging treatments of 2099 (C458) Al-Li alloy

Multistep artificial aging treatments coupled with various natural aging times for aluminum lithium 2099 alloy (previously called C458) are discussed to obtain mechanical tensile properties in the T6 condition that match those in the T861 condition, having a yield strength in the range of 414–490 MPa (60–71 ksi), an ultimate strength in the range of 496–538 MPa (72–78 ksi), and 10–13% elongation. Yield and ultimate tensile strengths from 90–100% of the strength of the as-received material (in the T861 condition) were obtained. The highest tensile strengths were consistently obtained with two-step, low-to-high temperature artificial aging treatments consisting of a first step at 120 °C (248 °F) for 12–24 h followed by a second step between 165 and 180 °C (329–356 °F) for 48–100 h. These T6-type heat treatments produced average yield and ultimate strengths in the longitudinal direction in the range of 428–472 MPa (62.1–68.5 ksi) and 487–523 MPa (70.6–75.9 ksi), respectively, as well as lower yield strength anisotropy when compared with the as-received material in the T861 condition.     

基于Incoloy800H钨极氩弧焊接头组织及其性能分析

在2 mm厚800H合金钨极氩弧焊试验的基础上,研究焊接接头的微观组织和析出相成分,并分析焊接接头的力学性能和抗晶间腐蚀性能,观察拉伸断口和晶间腐蚀试样的形貌。结果表明:焊缝组织为柱状晶和等轴晶,热影响区晶粒明显长大,焊接接头中有少量的TiN和富Cr相(Fe,Cr)_(23)C_6析出相存在;母材、热影响区和焊缝的HV硬度分别为1730、1526和1590 MPa;室温抗拉强度和延伸率分别为565.0 MPa、31.8%,均超过ASME标准关于800H合金规定值(450.0 MPa和30.0%),拉伸断裂为韧性断裂;焊接接头高温(650℃)抗拉强度和延伸率分别为394.5 MPa、15.5%,其断口是混合型断口;较接头组织,母材腐蚀更为严重,表面晶界开裂并伴有少量且尺寸较小的腐蚀坑,基体中TiN缺陷处易引起点蚀。     

GH2036高温合金平板裂纹闭合效应及裂纹扩展模型

为探明GH2036高温合金的低循环疲劳裂纹扩展机理,对GH2036高温合金平板在550℃、不同应力比下的低循环疲劳裂纹扩展特性进行了试验研究,采用数字图像相关(DIC)方法确定了GH2036高温合金的张开应力强度因子。结果表明,温度550℃、应力比大于0.7时GH2036高温合金无裂纹闭合现象,在此基础上建立了以残余裂尖张开位移、应力比为参量的GH2036高温合金裂纹闭合模型。而后,断口的SEM分析表明:随着应力比的增加,裂纹扩展区由穿晶断裂向沿晶断裂转化。最后,基于GH2036高温合金的裂纹闭合模型,建立了GH2036高温合金平板的低循环疲劳裂纹扩展寿命预测方法,与试验数据吻合良好,验证了方法的准确性。     

热处理对TC4-DT钛合金棒材组织和性能的影响

研究了热处理对TC4-DT合金φ300 mm棒材显微组织、拉伸性能、断裂韧性和疲劳裂纹扩展速率的影响.结果表明:经800℃×2 hAC简单退火、α+β相区固溶+时效、β相区固溶+时效处理后的TC4-DT的显微组织分别为等轴组织、双态组织和片状组织.等轴组织具有较好的拉伸性能、低的断裂韧性和高的疲劳裂纹扩展速率:双态组织与等轴组织相比较,具有较好的拉伸性能,较高的断裂韧性和较低的疲劳裂纹扩展速率:片状组织的拉伸强度低于双态组织和等轴组织,塑性最低,断裂韧性和疲劳裂纹扩展速率与双态组织的基本相同.总体来说,TC4-DT合金经α+β相区固溶+时效、β相区固溶+时效处理后可获得R_m≥3825 Mpa,R_(P0.2)≥750 Mpa,A_5≥8%,K℃≥90 Mpa ,疲劳裂纹扩展速率小于8×10~(-6)～9×10~(-6) mm/cycle的综合性能.     

The effects of rolling and sensitization treatments on the stress corrosion cracking of 304L stainless steel in salt-spray environment

U-bent and notched tensile tests in a 80 °C salt-spray environment were conducted to evaluate the effect of cold rolling at room temperature (CR), warm rolling at 150 °C (WR), and a sensitization at 650 °C/10 h (CRS and WRS) on the hydrogen embrittlement (HE) susceptibility of the 304L stainless steel. The CR specimen exhibited the highest crack growth rate with a greater number of short cracks found in the CRS specimen in U-bent tests. The CR specimen was resistant to HE in notched tensile tests relative to other specimens. Cracking in these specimens was more likely to initiate at the slip bands.     

Effect of temperature on fatigue crack growth in P92 steel

Fracture at high temperature has become a critical problem for such high temperature components as those used in power plants or oil refinery plants, because both high operating temperature and pressure are required for better thermal efficiency. Therefore, it is very important to approach such problems from the viewpoint of high temperature material properties. Since fatigue and creep are closely related to such components failures, the fracture behavior in high temperature components must be evaluated through fatigue and creep crack growth tests, and based on these results, better operating conditions can be determined. In this study, recently developed P92 (9Cr-2W) alloy steel, which is a high strength material for high temperature use, is investigated and its fatigue crack growth has been characterized by Paris law. A series of high temperature fatigue tests were carried out at 400, 500, 550, 600, 625, 650, and 700°C to verify the temperature effect. The results indicated that the Paris exponent remained at approximately the same value up to a certain temperature. From 600 to 700°C, creep rupture tests were conducted in order to investigate the creep behavior with temperature. Further analysis has also been carried out to investigate the effect of temperature on fracture mode shift, dimple formation, and its role in crack growth rate and deformability at high temperature.