残余应力与拘束对GH4169合金疲劳及蠕变-疲劳裂纹扩展速率影响研究

为深入理解残余应力与拘束在疲劳载荷下的交互作用,以镍基高温合金GH4169为研究对象,选用紧凑拉伸(CT)试样,对不同拘束CT试样的上方施加不同大小的预加载荷从而在裂尖产生不同应力。将该应力作为残余应力,系统研究残余应力和拘束交互作用下GH4169合金的疲劳和蠕变–疲劳裂纹扩展速率。结果表明：随着裂尖残余压应力的增加,不同拘束下GH4169合金的疲劳和蠕变–疲劳裂纹扩展速率均降低。与低拘束试样相比,高拘束试样的疲劳和蠕变–疲劳裂纹扩展速率对残余应力的变化更加敏感,这主要与裂尖Mises应力和垂直于裂纹扩展方向的正应力有关。与疲劳裂纹扩展速率相比,蠕变-疲劳裂纹扩展速率对残余应力的变化更加敏感。     

镍基高温合金GH4049高温疲劳小裂纹扩展规律的试验观察

对镍基高温合金GH4049在不同载荷与不同温度下疲劳小裂纹萌生和扩展进行了试验,利用复型技术和光学显微镜观测了裂纹尺寸演化全过程,发现高温疲劳损伤是一个多裂纹系统,且损伤起始于晶界,寿命前期是以裂纹萌生为主的均匀损伤,后期则为以裂纹扩展、合并为主的局部化损伤。     

陶瓷刀具高速车削GH4169高温合金切屑实验

针对陶瓷刀具WG300车削高温合金GH4169,设计了车削加工实验,利用扫描电镜（SEM）图和能谱分析（EDS）图对产生的切屑的形态和元素进行研究,得到了切削速度对切屑的影响规律,观察到刀具和工件在切削过程中发生元素的扩散现象.随着切削速度的增加,切屑出现显著的锯齿状,其成分中C的质量分数增多,Al和O元素没有显著变化,表明刀具中的Al2O3较为稳定.该研究对陶瓷刀具加工过程中的切削速度的选择具有指导和参考意义.     

粉末高温合金FGH97疲劳裂纹扩展行为

测定不同晶粒尺寸、γ'相以及不同Hf含量的粉末高温合金FGH97在650℃高温条件下的疲劳裂纹扩展速率,并将其与FGH95和FGH96两代粉末合金的疲劳裂纹扩展速率进行对比. 用定量分析的方法对FGH97合金在疲劳断裂各个阶段的行为特征进行分析. 较大晶粒尺寸的FGH97合金具有较低的裂纹扩展速率,合理的二次和三次γ'相匹配析出,可以获得较高的疲劳寿命;Hf元素的添加使合金的整体疲劳寿命增大;FGH97合金与FGH95和FGH96相比,具有较高的疲劳裂纹萌生抗力,更低的高温疲劳裂纹扩展速率.     

GH4169合金高温多轴非比例加载下疲劳断口特征

研究了总应变控制下比例加载和不同相位差(45°和90°)的非比例加载条件下GH4169镍基高温合金650℃双轴疲劳的断口特性.结果表明,比例加载时,裂纹在试样表面均匀萌生;随非比例度提高,裂纹萌生的数量明显减少.比例加载的断口表面有明显的撕裂条带,且沿径向扩展;而非比例加载时这些撕裂条带减少,相应地撕裂面增多,在相位差为90°时断口表面完全为撕裂面,且沿圆周方向扩展.在两裂纹扩展的交界处,发现有疲劳条纹,沿径向分布.在瞬间断裂区,随着非比例度的增加,韧窝逐渐加深,且撕裂面逐渐加大.     

高温合金涡轮盘材料的裂纹扩展速率

用直流电位研究了高温合金涡轮盘材料的裂纹扩展速率，结果表明：高温合金涡轮盘材料的裂纺展速率快慢，不完全取决于材料强度，更主要地取决于持久塑性，在考察高温合金涡轮盘材料的裂纹扩展时，不能认速率值ｄａ／ｄＮ的绝对值来衡量，还应看裂纹扩展速率曲线的斜率是否锐减或曲线出现明显的拐点，以及曲线所对应的应力强度因子△Ｋ的范围。     

GH864合金组织特征对裂纹扩展速率的影响

利用光学显微镜、场发射扫描电镜等手段,研究了GH864合金三种轧制态组织经热处理后的演变过程,分析了热处理后不同组织对室温冲击韧性及高温650℃裂纹扩展速率的影响.结果表明,GH864合金由初始轧制态组织经标准热处理后（1020℃,4h/空冷→845℃,4h/空冷→760℃,16h/空冷）获得的晶粒组织,其晶粒组织演变具有明显的一致性,而合金的晶界碳化物分布及基体γ＇强化相没有明显差别,其分布状态及尺寸大小基本一致.热处理后的晶粒尺寸越大,抗裂纹扩展能力越好,合金的室温冲击韧性越低;热处理后形成的项链状组织,对合金冲击韧性及裂纹扩展速率有较好的影响.     

GH586合金的晶界碳化物高温强化

通过对ＧＨ５８６合金在不同固溶处理温度下的金相组织观察,晶界碳化物萃取复型的透射电镜观察,定量相分析及８５０℃拉伸性能的测试,研究了晶界碳化物对合金高温拉伸性能的影响,探讨了高温下合金晶界碳化物的强化作用,并结合理论分析提出了晶界碳化物高温强化关系式。结果表明,该合金中均匀分布的细小晶界碳化物在高温下提高了合金强度;晶界碳化物对８５０℃屈服强度的贡献,用理论模型分析的结果与实验结果符合良好。     

带中心孔的镍基高温合金GH4049的高温疲劳短裂纹扩展规律

对疲劳试样GH4049镍基高温合金在同一载荷与不同温度下的疲劳短裂纹扩展进行了试验，利用复型技术和光学显微镜观测了裂纹形态演化全过程。发现应力集中条件下的高温疲劳短裂纹扩展主要是单裂系统破坏，随着温度升高，短裂纹逐渐变为多裂系统，并以多裂纹的合并形式进行最终破坏；扩展方式由穿晶到沿晶和穿晶的混合方式进行，温度越高，短裂纹起裂越早，裂纹平均长度越短，短裂纹扩展速率反而越慢。     

GH586合金的晶界碳化物高温强换

通过对GH586合金在不同固溶处理温度下的金相组织观察、晶界碳化物萃取复型的透射电镜观察、定量相分析及850℃拉伸性能的测试,研究了晶界碳化物对合金高温拉伸性能的影响.探讨了高温下合金晶界碳化物的强化作用,并结合理论分析提出了晶界碳化物高温强化关系式.结果表明,该合金中均匀分布的细小晶界碳化物在高温下提高了合金强度;晶界碳化物对850℃屈服强度的贡献,用理论模型分析的结果与实验结果符合良好.     

预蠕变损伤对高温疲劳宏观裂纹扩展的影响

针对ＳＵＳ３０４不锈钢光滑试棒预先导入１０７３ Ｋ·ｃｐ－ｔｙｐｅ条件下的预蠕变疲劳损伤，然后开小切口进行时间依存性 ９２３ Ｋ·ｃｐ－ｔｙｐｅ，１０７３ Ｋ·ｃｐ－ｔｙｐｅ及循环数依存性９２３ Ｋ·ｐｐ－ｔｙｐｅ的宏观裂纹扩展试验，考察了试棒内部因预蠕变疲劳而产生的大量的粒界微小裂纹对高温疲劳宏观裂纹扩展的影响．结果如下： １．预损伤加速了９２３ Ｋ·ｃｐ－ｔｙｐｅ下的蠕变裂纹扩展，对于同一蠕变Ｊ积分范围△Ｊｃ，损伤值越大，裂纹扩展速度ｄｌ／ｄＮ也越大．这种加速起因于主裂纹与微小裂纹的合体． ２．１０７３ Ｋ·ｃｐ－ｔｙｐｅ下的预损伤材料和处女材料的ｄｌ／ｄＮ在同一△Ｊｃ。下相等．即，损伤材料的裂纹扩展速度的上限值由１０７３ Ｋ·ｃｐ－ｔｙｐｅ下的处女材料的ｄｌ／ｄＮ－△Ｊｃ关系给出． ３．在９２３ Ｋ·ｐｐ－ｔｙｐｅ条件下，对于同一疲劳Ｊ积分范围△Ｊｆ，预损伤材料的ｄｌ／ｄＮ要比处女材料快１０倍左右．一般ｐｐ－ｔｙｐｅ的破坏形式为粒内破坏．预损伤材料的场合，因为试棒内部分布有大量的微小粒界裂纹，主裂纹便沿这些破坏阻抗最小的微小裂纹边合体边扩展，主要在粒界上扩展．即微小粒界裂纹是裂纹扩展阻抗减小的主因．     

Low cycle fatigue behavior of micro-grain casting K4169 superalloy at room temperature

The strain-controlled low cycle fatigue tests were carried out at 298 K for the newly developed micro-grain casting K4169 superalloy,and the cyclic stress response,deformation and fracture behaviors of the alloy were studied.The results show that the fatigue life of the alloy was increased by more than two times compared with other casting K4169 alloys.This can be partly attributed to grain refinement impeding crack initiation and propagation.When the strain amplitude was in plastic range(Δε     

Solute atom migration in GH4169 superalloy under electrostatic fields

Electric field treatment (EFT) was applied on GH4169 alloy during aging at 500–800℃ to investigate the microstructure and property variation of the alloy under the action of EFT. The results demonstrate that the short-distance diffusion of Al, Ti, and Nb atoms can be accelerated by EFT, which results in the coarsening of γ′ and γ″ phases. Meanwhile, lattice distortion can be caused by the segregation of Fe and Cr atoms, owing to the vacancy flows migrating toward the charged surfaces of the alloy. Therefore, the alloy is hardened by the application of EFT, even if the strength of the alloy is partly reduced, which is caused by precipitation coarsening.     

Interaction of fatigue and creep of GH33 under multi-axial stress at high temperature

Low-cycle fatigue experiments of tension-compression, torsion and tension-torsion with holding time were performed.The interaction law of creep and fatigue under multiaxial stress at high temperature was investigated, and the micro-mechanism of equilibrium diagrams was analyzed. A united equation of fatigue life under multiaxial stress was proposed.     

Interaction between crack and twins in TMS-82 superalloy during thermome chanical fatigue process

Thermomechanical fatigue behavior of a nickel base single crystal superalloy TMS-82 has been investigated.It was found that the micropores in the alloy tend to initiate large amounts of deformation twins and the crack causes many twins to occur during its propagation.It is postulated that these twins around the micropores or the crack are induced by the stress eld of the micropores or the crack tip,respectively.A thermodynamic model is adopted linking the twin formation energy with the stress eld around the crack tip,which explains the observed results with good consistency.The in uencing factors for a crack to stimulate twins around it are shown by the model,which might provide possible ways to enhance the alloy’s thermomechanical fatigue performance.     

Effect of microstructures restoration on high temperature fatigue behavior of DZ125 superalloy

Combination of hot isostatic pressing(HIP) and rejuvenation heat treatment(RHT) technology was used to restore creep-damaged DZ125 directional solidified superalloy, and the influence of microstructure restoration on high temperature fatigue behavior of the samples was explored. The results show that the HIP+RHT process could effectively heal internal cavities and recover the degraded γ’ phase in creep-damaged DZ125 superalloy to cubic particles similar as in as-received sample. After restoratio...     

高速列车制动盘表面裂纹的扩展特性

分析了制动盘在运行过程中的载荷特征,采用有限元法模拟制动盘在不同制动工况下的热应力分布,发现反复制动形成的拉压应力循环是裂纹扩展的主要驱动力.依据制动盘裂纹剖面的形状特征,采用三维裂纹扩展软件FRANC3D建立了裂纹扩展模型,研究了盘面裂纹的应力强度因子随裂纹长度的变化规律.结合疲劳裂纹扩展理论和裂纹扩展门槛值,估算了临界裂纹尺寸和扩展寿命,以及不同裂纹尺寸扩展到临界长度时的运营里程.研究结果可为制动盘裂纹容限的制定提供参考.     

Aging behavior and fatigue crack propagation of high Zn-containing Al-Zn-Mg-Cu alloys with zinc variation

In the present work, the influence of two-step aging treatments on hardness, electrical conductivity and mechanical properties of two high Zn-containing Al-Zn-Mg-Cu alloys with zinc content variation was investigated and the detailed T76 aging parameters were proposed. The microstructure of the precipitates were studied by transmission electron microscopy (TEM) and high-resolution transmission electron microscopy (HREM) and then quantitatively investigated with the aid of an image analysis. The fatigue performances were researched by the fatigue crack propagation (FCP) rate test and fracture morphology was observed with scanning electron microscopy (SEM). The results show that the matrix precipitate size distributions of both alloys had significant difference, so as to fatigue crack propagation rates and fracture appearance. The shear and bypass mechanisms of dislocation-precipitate interactions were employed to explain the difference. Among the shearable precipitates, the proportion of larger size precipitates for the higher zinc content alloy is bigger than that for the lower zinc content alloy. The coarse shearable precipitates hinder the propagation of the fatigue cracks, leading to inferior FCP rate. For both alloys, the shear mechanism possesses the dominant factor, finally causing a preponderance in the FCP resistance for the higher zinc content alloy than the lower one.