钴磷镀层表面热疲劳裂纹的萌生及扩展机理

在自约束型热疲劳试验机上对化学镀钴磷合金镀层进行了热疲劳试验,采用光学显微镜、扫描电子显微镜研究了在热应力作用下镀层表面热疲劳裂纹萌生、扩展的方式和形态。结果表明:200次冷热循环后,V型缺口处发生塑性变形,并且随冷热循环的进行,热疲劳裂纹由缺口底部萌生并沿着循环方向扩展。重点分析了钴磷合金镀层表面热疲劳裂纹的萌生及扩展机理。     

GH761涡轮盘650℃疲劳/蠕变交互作用下的裂纹扩展速率

试验了GH761涡轮盘在650℃疲劳／蠕变交互作用下的裂纹扩展速率，试验结果表明：GH761合金在650℃初始应力强度△K（K）=30MN/m^3/2，保载90s时，裂纹扩展率较快，曲线斜率变化不明显。     

长期时效和晶粒度对GH333和GH128合金热疲劳的影响

本文研究了燃气涡轮发动机燃烧部件用GH333和GH128合金长期时效和晶粒度对热疲劳性能的影响。随时效时间延长,抗热疲劳性能明显下降,在850℃时效至2000小时,裂纹扩展速度较固溶态增大了3～4倍。从裂纹长度和循环次数及时效时间,推导出L-N和L-τ及裂纹扩展速度dL/dN的表达式。长期时效后的板材,再经固溶处理,其抗热疲劳性能基本上得到恢复。采用适当固溶温度处理,该二合金晶粒度适中,可获得强度、塑性和抗热疲劳性能较好的配合     

循环条件对YG20硬质合金热冲击裂纹扩展的影响

研究了循环条件对ＹＧ２０硬质合金热冲击裂纹扩展的影响。结果表明，随着循环温度的升高和冷却速率的增加，萌纹萌生的孕育期缩短，裂纹扩展速率增加。扫描电镜观察发现，热冲击断口存在疲劳条纹。     

GH4169合金高温疲劳裂纹扩展的微观损伤机制

空气环境对高温合金在高温下的损伤行为有显著影响.为了研究标准热处理态GH4169合金在高温疲劳裂纹扩展过程中的微观损伤机制,在空气环境中进行650℃、初始应力强度因子幅ΔK=30 MPa·m1/2和应力比R=0.05的低周疲劳裂纹扩展试验.使用扫描电镜(SEM)及能谱(EDS)对试样的断口、外表面和剖面进行观察和分析.实验结果表明:疲劳主裂纹以沿晶方式萌生并扩展,随后沿晶二次裂纹出现,并且其数量和长度沿主裂纹方向逐渐增加,进入快速扩展阶段后,断口呈现韧窝组织形貌;在裂纹扩展过程中,δ相与基体的界面发生氧化,使得沿晶二次裂纹沿界面扩展并产生偏折,从而起到阻碍二次裂纹扩展的作用;试样外表面的主裂纹周围出现晶界氧化损伤区,其尺寸和晶界开裂程度沿主裂纹扩展方向逐渐增大.      

7475-T7351铝合金抗疲劳性能研究

采用旋转弯曲疲劳试验、轴向加载疲劳试验、疲劳裂纹扩展速率试验等疲劳性能测试方法,研究了7475-T7351铝合金厚板的疲劳性能.并通过透射电镜(TEM)和扫描电镜(SEM)分析了该合金的显微组织和疲劳断口形貌.结果表明:7475-T7351铝合金具有良好的耐疲劳损伤性能,光滑试样(Kt=1)在室温旋转弯曲和高温轴向加载条件下的疲劳极限分别为180.0和345.0 MPa,缺口试样(Kt=2.2)在室温旋转弯曲加载条件下的疲劳极限为91.9 MPa;合金厚板材料在高温下缺口敏感性有所降低;国产材料裂纹扩展速率随应力比增加而增大,裂纹扩展门槛值减小;国产7475铝合金与进口材料在裂纹稳定扩展阶段裂纹扩展行为基本相当;在近门槛值附近不同应力比下的裂纹扩展门槛值略有差别.     

温度与应力比对6061铝合金疲劳裂纹扩展行为的影响

为了研究温度与应力比对航空铝合金疲劳裂纹扩展行为的影响,利用电液伺服疲劳试验机对6061铝合金材料开展了不同温度(室温、-70、150 ℃)、应力比(0.1、0.5)条件下的疲劳裂纹扩展速率试验,获得不同条件下的疲劳裂纹扩展速率曲线,揭示温度与应力比对疲劳裂纹扩展的影响规律。结果表明,在相同应力比下,室温与高温150 ℃下的疲劳裂纹扩展速率曲线(da/dN-ΔK)基本一致,低温-70 ℃下的疲劳门槛值与疲劳裂纹扩展速率明显提高,这表明低温环境下6061铝合金材料具有较高的抗疲劳裂纹扩展性能;在相同温度下,随着应力比的增大,疲劳门槛值降低,疲劳裂纹扩展速率升高。讨论了温度与应力比对疲劳裂纹扩展行为影响的可能原因。     

基于直流电压降法的传热管疲劳裂纹扩展速率测量

介绍了基于直流电压降法测量蒸汽发生器传热管690合金轴向疲劳裂纹扩展速率的销加载拉伸方法.该方法与其他方法相比较,可以直接采用原始管状材料,在线连续测量管状试样在不同应力强度因子下的疲劳裂纹扩展.通过对标准紧凑拉伸试样的类比分析,建立传热管试样的销加载拉伸模型,并对该模型进行电学和力学有限元模拟分析,确定直流电压降数据采集方法.验证试验采用核电蒸汽发生器用690合金传热管,分别研究了室温和高温325℃空气中载荷和温度对材料疲劳裂纹扩展速率的影响,试验结果采用Paris-Erdogan公式进行拟合,吻合度较好.扫描电镜下观察端口形貌,疲劳裂纹的扩展为穿晶形式,在穿晶断口上观察到明显的疲劳辉纹和微塑性区.      

温度对一种高固溶强化β钛合金损伤行为的影响

Ti25V15Cr0.3Si合金含有40%左右的合金元素,是一种高固溶强化的β钛合金。测试了Ti25V15Cr0.3Si合金在室温(25℃)至600℃下的裂纹扩展性能,发现随着温度升高,裂纹扩展速率增大。与Ti6Al4V和β21S合金相比,室温下Ti25V15Cr0.3Si合金的裂纹扩展速率高于Ti6Al4V而低于β21S合金。600℃高温下,Ti25V15Cr0.3Si合金的裂纹扩展速率与β21S在650℃时的水平相当。研究结果表明,合金的屈服强度、弹性模量、断裂韧性、氧化性能和组织结构特征综合影响着Ti25V15Cr0.3Si合金的裂纹扩展损伤行为。从室温到300℃,随温度的升高,Ti25V15Cr0.3Si合金的屈服强度和弹性模量降低同时断裂韧性升高,因此裂纹扩展速率变化不明显;而从500～600℃,温度升高氧化加剧,合金疲劳裂纹扩展速率明显增加。与Ti6Al4V合金相比,室温下,Ti25V15Cr0.3Si合金相对于Ti6Al4V合金具有较低的弹性模量以及等轴的β组织,裂纹扩展速率较高。而与β21S合金相比,Ti25V15Cr0.3Si合金的屈服强度和弹性模量高于β21S合金,因此裂纹扩展速率较低。6...     

GH4720Li合金中温区低周疲劳行为研究

奥氏体沉淀强化GH4720Li合金用于制备航空发动机涡轮盘,其服役条件下的疲劳性能是当前研究的热点.研究了GH4720Li合金在中温区(450和550 ℃)不同应变条件下的低周疲劳行为.结果表明,GH4720Li合金的剪切模量和杨氏模量随着温度的升高而不断降低,但是中温区的抗拉强度和屈服强度不随温度而剧烈下降.GH47...     

Thermal Fatigue Behavior and Cracking Characteristics of High Si-Mo Nodular Cast Iron for Exhaust Manifolds

 The thermal fatigue cracking behavior of high Si-Mo nodular cast iron (NCI) is investigated by means of optical microscope (OM), scanning electron microscope (SEM) and energy dispersive spectroscope (EDS), in order to find a new material used in exhaust manifolds in First Automotive Works (FAW). Nodular cast irons with silicon content about 4. 7%, in combination with up to 1. 1% molybdenum, were produced by Jilin University and FAW. The repeated heating/cooling test was performed under cyclic heating at various maximum heating temperatures (Tmax) ranging from 800 to 900 ℃. Experimental results indicate that the thermal fatigue cracking resistance of high Si-Mo NCI decreases with increasing the maximum heating temperature. The periods for crack initiation are 24-36, 40-50 and 70-90 times associated with heating temperature of 900, 850 and 800 ℃, respectively, when the holding time is about 10 min at Tmax. When thermal fatigue cracking occurs, the cracking always initiates at the bigger surface of specimen. The major positions of cracks propagation are generally at the eutectic oxide boundary region and the region of the graphite disappearance. At the same time, the oxidation may accelerate crack initiation and propagation. On the other hand, micro-crack number varied from large to little because of shielding effect. As exhaust manifolds, the reasonable working temperature of high Si-Mo NCI is no more than 840 ℃ by test and analysis.     

Effect of Isothermal Annealing on Nano Ti-Carbides Precipitation

Transmission electron microscopy was used to investigate the effect of isothermal holding temperature and time on the nano Ti-precipitates.A holding temperature was varied systematically from 400℃ to 1200℃.The isothermal holding was continued for 30s,300s and 900s,respectively.Nano carbides of (Ti,Nb)C were precipitated significantly at 900℃.The size of carbides was approximately 10nm at 30s holding and increased to 20～30nm at 900s holding.Isothermal holding at 1000℃ showed the increased amount of carbides larger than 100nm.At 800℃,nano (Ti,Nb)C was not observed at 30s and it was examined at 300s.The size of nano (Ti,Nb)C was smaller than that of 900℃.As the isothermal temperature decreased to 700 ℃,the nano (Ti,Nb)C was only seen at 900s holding and the size of carbides was smaller than 10nm.Nano (Ti,Nb)C was disappeared at isothermal holding below 600℃.The kinetics of nano (Ti,Nb)C precipitation were studied as a function of isothermal holding temperature and time,respectively,using the precipitate growth equations.     

Thermal fatigue of a heat-resistant Fe-0.45C-26Cr-33Ni-2Si-2Nb alloy

The thermal fatigue of a heat-resistant Fe-0.45C-26Cr-33Ni-2Si-2Nb alloy is studied during thermal cycling in the temperature range 50–900°C up to 1000 cycles. The alloy is investigated in the initial as-cast state and after isothermal annealing during 1000 h at a temperature of 800, 900, 1000, or 1100°C; these conditions imitate the temperature conditions of operation and the structural state of various layers in a reaction pipe in the radiant furnace coils of ethylene production installations. After isothermal annealing, the thermal fatigue life of the alloy is found to decrease by a factor of 1.7–1.2 as compared to the initial as-cast state. It is shown that isothermal annealing and subsequent thermal cycling lead to the formation of carbide precipitates of various sizes in the alloy structure that affect the thermal fatigue life of the alloy. Thermal fatigue cracks are shown to form and grow predominantly at the sites of accumulation of fine carbide precipitates. Coarse (>10 μm) precipitates retard crack growth, and cracks branch near such precipitates.     

粉末高温合金Udimet720Li γ′强化相析出行为

采用气淬炉模拟了粉末高温合金Udimet720Li经空冷、风冷及油冷等不同冷却路径的固溶处理过程,测试了经过两级时效处理的合金在650 ℃的拉伸性能,研究了拉伸变形后的位错组态,分析了冷却速率对γ′强化相析出规律及力学性能的影响。结果表明:粉末高温合金Udimet720Li的析出相强化机制为位错切过机制,二次γ′相尺寸越小,合金强度越高。合金二次γ′相的形核析出温度区间为900～1000 ℃,其尺寸与合金在该温度范围内的冷却速率成反比,冷却速率越大,γ′相尺寸越小,当冷速高于100 ℃/min时,合金强度达到应用要求。推荐粉末Udimet720Li合金盘件固溶处理的冷却方式为:在1000 ℃以上保持低冷却速率来降低淬火应力,然后选择油浴作为盘件淬火的冷却方式,入油温度应在1000 ℃左右。     

一种[011]取向镍基单晶合金的蠕变断裂

研究了[011]取向的镍基单晶高温合金在750~980℃温度范围和200~680 MPa应力下的蠕变断裂特征.在扫描电镜上对各种实验状态下的蠕变断口和纵向剖面进行了详细观察.研究发现:在低温750℃和中温870℃不同初始蠕变应力条件下,枝晶间区亚晶界处不规则γ＇/γ界面是裂纹主要萌生场所,这些已萌生的裂纹在与外加应力轴垂直的（011）面上沿〈110〉和〈100〉两个方向扩展;980℃不同初始应力条件下,裂纹主要在合金中显微疏松孔洞处萌生,沿与外应力轴垂直的方向扩展.观察750℃和870℃不同应力状态蠕变试样的纵向剖面,对亚晶界区不规则γ＇相面积分数的测量和计算表明,用面积分数表征该合金[011]取向在中低温状态下的蠕变损伤程度是可行的.      

Isothermal fatigue of an aluminide-coated single-crystal superalloy: Part I

The isothermal fatigue behavior of a high-activity aluminide-coated single-crystal superalloy was studied in air at test temperatures of 600 °, 800 °, and 1000 °. Tests were performed using cylindrical specimens under strain control at ≈0.25 Hz; total strain ranges from 0.5 to 1.6 pct were investigated. At 600 °, crack initiation occurred at brittle coating cracks, which led to a significant reduction in fatigue life compared to the uncoated alloy. Fatigue cracks grew from the brittle coating cracks initially in a stage II manner with a subsequent transition to crystallographic stage I fatigue. At 800 ° and 1000 °, the coating failed quickly by a fatigue process due to the drastic reduction in strength above 750 °, the ductile-brittle transition temperature. These cracks were arrested or slowed by oxidation at the coating-substrate interface and only led to a detriment in life relative to the uncoated material for total strain ranges of 1.2 pct and above 800 °. The presence of the coating was beneficial at 800 ° for total strain ranges less than 1.2 pct. No effect of the coating was observed at 1000 °. Crack growth in the substrate at 800 ° was similar to 600 °; at 1000 °, greater plasticity and oxidation were observed and cracks grew exclusively in a stage II manner. Formerly Research Student, Department of Materials Science and Metallurgy, University of Cambridge. Formerly Lecturer, Department of Materials Science and Metallurgy, University of Cambridge CB2 3QZ, United Kingdom.     

热连轧GH4169合金晶粒的长大规律

对热连轧GH4169合金在固溶处理过程中晶粒长大规律进行了系统的研究。研究结果表明,该合金δ相溶解温度在990~1 000℃之间,δ相对晶粒长大有显著阻碍作用,在低于δ相溶解温度进行固溶处理时,析出的δ相使得晶粒长大缓慢;在高于δ相溶解温度以上时,晶粒随温度的升高快速长大。晶粒长大动力学表明：在高于δ相固溶线温度以上进...     

Isothermal fatigue of an aluminide-coated single-crystal superalloy: Part II. effects of brittle precracking

The effect of brittle coating precracking on the fatigue behavior of a high-activity aluminide-coated single-crystal nickel-base superalloy has been studied using hollow cylindrical specimens at test temperatures of 600 °, 800 °, and 1000 °. Three types of precrack were studied: narrow precracks formed at room temperature, wide precracks formed at room temperature, and narrow precracks formed at elevated temperature. The effect of precracking on fatigue life at 600 ° was found to depend strongly on the type of precrack. No failure was observed for specimens with narrow room-temperature precracks because of crack arrestvia an oxidation-induced crack closure mechanism, while the behavior of wide precracks and precracks formed at elevated temperature mirrored the non-precracked behavior. Crack retardation also occurred for narrow room-temperature precracks tested at 800 °—in this case, fatigue cracks leading to failure initiated in a layer of recrystallized grains on the inside surface of the specimen. A significant reduction in fatigue life at 800 ° relative to non-precracked specimens was observed for wide precracks and elevated temperature precracks. The presence of precracks bypassed the initiation and growth of coating fatigue cracks necessary for failure in non-precracked material. No effect of precracking was observed at 1000 °. Formerly Research Student, Department of Materials Science and Metallurgy, University of Cambridge. Formerly Lecturer, Department of Materials Science and Metallurgy, University of Cambridge CB2 3QZ, United Kingdom.     

双相变回温温度对钢组织及其热塑性的影响

含铌钢连铸过程极易产生铸坯角部横裂纹。对连铸坯角部实施γ→α→γ双相变控冷工艺,可提高其组织的高温热塑性而减少裂纹产生。其中,α→γ相变阶段的回温温度是影响双相变控冷工艺实施效果的重要参数。通过Gleeble热模拟与金相观察、析出物透射以及断口扫描相结合的检测手段,研究分析了双相变过程回温温度对Q345D-Nb钢组织演变及其热塑性的影响规律。结果表明,回温温度为850℃时的奥氏体晶粒相比传统冷却工艺下的晶粒尺寸未产生细化,平均晶粒尺寸为502.2μm;回温温度升至900℃时,回温奥氏体出现了明显的混晶现象;当回温温度达到950℃时,晶粒细化至61.2μm;当回温温度达到1 000℃时,回温奥氏体晶粒出现了一定程度粗化,相比950℃回温温度下的奥氏体平均晶粒尺寸增加了38.07%。传统冷却工艺和不同回温温度时的双相变控冷工艺(回温温度为850、900、950、1 000℃),钢组织在700～900℃温度区内的断面收缩率最低值分别为29.6%、45.0%、56.3%、68.2%、63.2%。在传统冷却工艺下,钢组织在750℃时晶界铁素体膜的厚度为20～25μm,且碳氮化物呈大尺寸链状分布,...     

改进310奥氏体不锈钢长期时效后的组织与性能

借助扫描电子显微镜、透射电子显微镜以及高温、室温拉伸和硬度测试研究了实验室研发的改进310奥氏体不锈钢在700℃长期时效后的组织与性能.700℃时效1000 h后,实验钢在晶界和晶内析出了大量(Cr,Fe,Mo)₂₃C₆、(Cr,Fe)₂₃C₆、σ相和少量的χ相.析出相对实验钢的室温力学性能有明显的强化作用.强度增加,硬度升高20 Hv,同时延伸率仍保持在30%以上.高温下,析出强化效应减弱,延伸率轻微下降.通过断口表面和剖面观察发现,时效1000 h后,实验钢的高温拉伸断口为韧性断裂,未观察到裂纹和孔洞;而室温拉伸断口为脆性断裂,断口附近则观察到σ相中出现裂纹和孔洞.从σ相的脆-韧转变和实验钢基体的室温和高温强度的不同,讨论了在室温拉伸过程中产生裂纹和孔洞的原因,以及时效对室温和高温力学行为的不同影响.