Fatigue crack propagation behavior of K40S cobalt-base superalloy at elevated temperature

Fatigue crack propagation behavior of K40S cobalt-base superalloy under ambient atmosphere at 700 ℃ and 900 ℃ was investigated. The detailed fatigue crack propagation and fracture mechanism under the alternating loads were studied. The results show that, there is a defined threshold for K40S alloy at elevated temperatures. The fatigue threshold is 23.9 MPa·m 1/2 at 700 ℃ and 12 MPa·m 1/2 at 900 ℃. The significant decrease of the threshold with increasing temperature is associated with the oxidation induced embrittlement at crack tip. Observation on the fatigue fracture surfaces indicates a ductile fracture mechanism related to the fatigue crack growth.

Crack initiation and propagation induced by inclusions in a nickel-base P/M superalloy under fatigue load

In situ fatigue tests in special designed SEM were conducted to trace the whole process of crack initiation and propagation fill to fracture in mckel-base P/M superalloy seeded inclusions. The experimental results show that non-metallic inclusions can induce crack initiation. When the inclusion size is larger than the critical one, the crack can propagate as the main crack that induces the specimen to fracture. As a result, the LCF life of the specimen decreases.

EFFECT OF SULPHURIZING-OXIDIZING ENVIRONMENT ON CREEP CRACK GROWTH OF Ni-BASE SUPERALLOY GH30

An investigation was made on the creep crack growth behaviour under static load at 1023 K for Ni-base superalloy GH30 exposed to air and air+10% SO_2.The results showed that in the region of low stress intensity factor,the creep crack growth rate is higher in air+10% SO_2 than in air only,while in the high region,it is reverse.The fractograph of specimens has been analyzed,and the mechanism of creep crack growth together with the influences of sul- phur and oxygen has been discussed as well.

FATIGUE CRACK PROPAGATION OF Ni-BASE SUPERALLOYS

Time-dependent Fatigue Crack Propagation (FCP) behaviors of five Ni-base superalloys were investigated at various temperatures under fatigue with various holding times and sustained loading conditions. The new concept of damage zone is defined and employed to evaluate the alloys' resistance to hold-time FCP. A special testing procedure is designed to get the maximum damage zone of the alloys. Udimet 720 and Waspaloy show shorter damage zones than alloys 706 and 718. The fractographical analyses show that the fracture surfaces of the specimens under hold-time fatigue conditions are mixtures with intergranular and transgranular modes. As the extension of holding time per cycle, the portion of intergranular fracture increases, The effects of loading stress intensity, temperature, holding time, alloy chemistry, and alloy mi-crostructure on damage zone and the crack growth behaviors are studied. Hold-time usually increases the alloy's FCP rate, but there are few exemptions. For instance, the steady state hold-time FCP rate of Waspaloy at 760℃ is lower than that without hold-time. The beneficial effect of hold-time was attributed to the creep caused stress relaxation during the hold-time.

Laser repairing surface crack of Ni-based superalloy components

Surface crack of components of the cast nickel base superalloy was repaired with twin laser beams under proper technological conditions. One laser beam was used to melt the substrate material of crack, and the other to fill in powder material to the crack region. The experimental results show that the surface crack with the width of 0.1 ～ 0.3?mm could be repaired under the laser power of 3?kW and the scanning speed of 6 ～ 8?mm/s. The repaired deepness of crack region is below 6.5?mm. The microstructure of repaired region is the cellular crystal, columnar crystal dendrite crystal from the transition region to the top filled layer. The phases in repaired region mainly consisted of supersaturated α Co with plenty of Ni, some Cr and Al, Cr 23 C 6, Co 2B, Co Ni Mo, Ni 4B 3, TiSi and VSi. The hardness of filled layer in repaired region ranged from HV 0.2 450 to HV 0.2 500, and the hardness decreases gradually from the filled layer to joined zone.

AN IN SITU STUDY ON DEFORMATION TWINNING NEAR CRACK TIP IN TWO－PHASE TiAl－BASE ALIOY

An in situ study of twinning at crack tip in a TiAl-base alloy has been performed.The result shows that twinning with long shear vector(2/6) [112] can generate on(111) plane, even though usually it is very difficult to occur because of the high energy barrier. It was further shown that (1/6) [112](111) twinning is considerably easier to generate. Furthermore,(1/2)<110) ordinary dislocations were very active and dominated nearly the whole plastic zone, in spite of low Schmid factors. On the other hand, however <101) and (1/2) <112] superdislocations with higher Schmid factors can hardly be observed.

EFFECT OF Mg AND Zr ADDITION ON CREEP CRACK GROWTH BEHAVIOUR OF A Ni-BASE SUPERALLOY

The creep crack growth(CCG)and the time to carck initiation and rupture of specimen (t_(rc)and t_r)were measured by means of electrical potential method on single edge notched specimens at 700℃.The field near the crack tip under steady-state creep was represented by energy rate integral(C~*),and the CCG rate as a function of C~* has been obtained.The agreement between the predicted and observed t_(rc)values is quite good.It was found that the addition of small amount of Mg and Zr in the alloys causes t_(rc)and t_r of the specimens to in- crease significantly.

Effect of Lamellar Orientation on Crack Paths in PST Crystals of γ-TiAl BasedAlloys

The effect of lamellar orientation on crack paths in PST crystals of y-TiAl based alloys was investigated by in-situ SEM technique. The results indicate that the crack paths in PST crystals of y-TiAl based alloys are strongly dependent on lamellar orientation ofPST crystals, and the differently oriented PST crystals show different nucleation and propagation mechanisms of crack, resulting in different levels of fracture toughness.

动车组抗蛇形减震器底座裂纹原因分析

针对动车组抗蛇形减振器在例行维修中发现的裂纹缺陷,借助显微镜、扫描电镜、能谱分析对裂纹缺陷区域的显微组织进行观察和分析。结果表明,构件裂纹附近存在多处晶间腐蚀缺陷;裂纹的开裂方式以沿晶疲劳开裂为主,并伴生应力腐蚀开裂;因断口经历了腐蚀过程,不能排除裂纹是源于腐蚀开裂;未腐蚀的断口界面则表现出疲劳失效开裂行为。

基础激励下裂纹梁结构疲劳寿命预测模型

为了发展基于模型的裂纹梁结构疲劳寿命预测方法,提出了一种新的三维裂纹梁单元刚度矩阵。基于该刚度矩阵,建立基础激励下裂纹梁结构的三维有限元模型。推导三维裂纹梁单元的应力强度因子,建立三维裂纹梁单元的疲劳裂纹扩展模型。采用振动响应与裂纹扩展增量交互计算方法,计算循环载荷作用下裂纹梁结构的疲劳寿命。研究结果表明:裂纹梁结构寿命预测模型较好地体现了疲劳裂纹扩展寿命与基础激励参数、结构参数和裂纹参数之间的内在关系,反映了基础激励对裂纹梁结构疲劳寿命的影响。最后通过实验对模型进行了验证。

基于EBM增材制造CoNi基高温合金组织与力学性能

增材制造技术为发展高性能高温合金材料及部件提供了新的途径。本工作开发一种适于增材制造工艺条件的γ′相强化CoNi基高温合金,并结合电子束熔化(electron beam melting,EBM)技术的工艺参数优化,制备出无裂纹的合金块体材料。结果表明:扫描速度为2000 mm/s时,合金孔隙率最低,约为0.14%;打印态CoNi基合金显微组织为沿<001>方向生长的柱状晶粒,平均晶粒宽度约为235μm,γ′相体积分数约为30%;经过热等静压及固溶时效处理后,孔隙率进一步降低至约0.09%,柱状晶粒基本没有变化;γ′相的平均尺寸为(70±18)nm,体积分数为(32±3.6)%。室温拉伸实验结果表明,增材制造γʹ相强化CoNi基高温合金展示出优异的强塑性配合,展示出良好的工业应用前景。

碱含量对水泥基材料开裂敏感性的影响

选择低热硅酸盐水泥、中热硅酸盐水泥和普通硅酸盐水泥作为研究对象,利用外掺Na2SO4和K_(2)SO_(4)将其总碱含量调节至0.8%和1.2%,利用椭圆环法,并从干燥收缩性能、水化产物形貌、显微硬度及水化产物微观力学的角度,探究了碱对不同水泥基材料开裂敏感性的影响。结果表明:随着碱含量的提高,不同水泥基材料的开裂敏感性增加;低热硅酸盐水泥具有较高的抗裂能力,且适当地提高碱含量,有助于提高其抗裂性能;干燥收缩性并不能完全揭示碱对不同水泥基材料开裂敏感性的影响机制。碱对不同水泥基材料开裂敏感性的提高还与其微观特性有关,通过促使水化产物形貌发生转变,提高其显微硬度,降低水泥基材料浆体适应变形的能力;通过降低唯一具有胶凝特性的水化硅酸钙(C-S-H)簇间粘结力,降低水泥基材料浆体抵抗开裂的能力。

聚丙烯纤维磷石膏胶结体早期力学强度特性及增韧机理研究

在传统水泥基复合材料的研究领域,纤维增强了材料的强度、韧性、延展性和抗裂性。为了提高磷石膏胶结体的早期强度,掺入聚丙烯纤维作为增强剂,开展了掺纤维磷石膏胶结体制备试验以及单轴抗压强度试验,分析了纤维对磷石膏胶结体破坏规律的影响,并通过SEM探究了纤维对磷石膏胶结体的增韧机理。研究结果表明:随纤维掺量增加磷石膏胶结体单轴抗压强度呈先增加后降低的趋势,且纤维最优掺量为1%;掺入纤维的磷石膏胶结体能延缓峰值抗压强度达到时间且破坏时的峰值应力更大,未掺入纤维的磷石膏胶结体在荷载超过应力峰值后快速失稳,掺入聚丙烯纤维的磷石膏胶结体则呈缓慢降低趋势;随着纤维的掺入,磷石膏胶结体的裂纹数量逐渐减少,且裂而不断,磷石膏胶结体的延性变形明显;微观下聚丙烯纤维表面附着有絮团状水化产物,且在磷石膏胶结体固结过程中相互缠结形成稳定的网状结构。研究成果可为磷石膏基复合材料在固废胶结充填现场的应用提供一定参考。

高温模拟压水堆一回路水中枝晶取向对Inconel 182镍基合金焊接金属应力腐蚀开裂的影响

在模拟压水堆(PWR)一回路高温水中对Inconel182镍基合金焊接金属进行了应力腐蚀开裂(SCC)试验,研究了枝晶取向对其SCC行为的影响。结果表明:在320℃下模拟压水堆一回路水中,182合金LT取向试样断口上出现全面沿晶应力腐蚀裂纹扩展带,其平均裂纹扩展速率以及最大裂纹扩展速率均大于290℃下相同试样,表明在模拟压水堆一回路水中升高温度对182合金焊接金属应力腐蚀裂纹扩展有促进作用;290℃下182合金LT取向试样的平均裂纹扩展速率、最大裂纹扩展速率以及裂纹扩展区宽度占比均大于TL取向试样,表明裂纹沿LT枝晶取向更容易扩展。

原油直接催化裂解UPC工艺过程模拟与反应参数多目标优化

原油直接催化裂解技术可以实现从原油到三烯(乙烯、丙烯、丁烯)、三苯(苯、甲苯、二甲苯)的一步跨越,对我国炼化行业的转型升级具有重要意义。以全馏分石蜡基中原原油(159~780℃)为原料,采用混合馏分结构与分子组成集总建模策略,对原油直接催化裂解制烯烃(UPC)反应过程进行建模与工艺参数校准,并基于工业试验数据验证了其准确性。以多产烯烃、控制焦炭生成为目的,利用NSGA-Ⅲ多目标优化算法对模型进行了优化,得到优化后的操作参数。采用优化后的操作参数,即在第一段预热闪蒸温度为194.32℃、第二段预热闪蒸温度为228.16℃、第一段提升管反应器出口温度为615.73℃、第二段提升管反应器出口温度为622.59℃的条件下,UPC工艺得到的乙烯和丙烯收率之和为53.367%,焦炭收率为8.311%。此外,由于现行税费体系燃料型工艺路线税收贡献明显高于化工型工艺路线,UPC工艺参数优化后,烯烃收率大幅度提升,燃料油收率大幅度下降,原油生产总值降低44.30元t。

加热-冷却过程中花岗岩细观热破裂机制

由于高温试验设备的限制,在实验室中研究岩石真实热破裂规律通常需要依据冷却后试样的细微观结构观测结果来进行分析推断,无法获得热破裂的实时动态演化过程。为此,基于考虑温度和裂纹滑移效应的节理本构关系,构建花岗岩热力耦合UDEC晶粒模型,以深入探究加热和冷却过程中花岗岩的实时热破裂行为。研究发现,在加热状态下,花岗岩热诱导微裂纹在75℃左右开始萌生,随着温度的升高,微裂纹数量在α→β石英相变温度附近快速达到峰值,但微裂纹密度在600℃降温到25℃的冷却过程中并没有明显变化。虽然冷却效应引起的裂纹数量变化可以忽略不计,但会导致裂纹开度的增加或减少。在加热过程中,微裂纹的萌生主要是由于相邻晶粒的热膨胀不同导致局部应力累积造成的。而石英高温相变引起的细微观结构变化可以增强不同晶粒之间的相互作用,导致晶粒尺度上的压缩和剪切运动加剧,使得热应力裂纹继续变形拓展。在冷却过程中,由于加热过程中热破裂导致的细微观应力释放和冷却效应导致的不同矿物晶体收缩,使得微裂纹的数量虽然不变,但其形态却能发生较为明显的变化,从而使得冷却后花岗岩的宏观应力-应变行为受到很大影响。基于离散元数值模拟对花岗岩热力耦合试验结果作出了细微观阐释,揭示了加热和冷却过程中花岗岩的实时热破裂机制,进一步加深了对高温岩石热力耦合规律的理解。

多尺度钢纤维混杂增强水泥基材料抗冲击性能及阻裂能力

为更好地研究钢纤维混杂方式对水泥基材料的增强作用,本研究使用长度分别为6 mm(S)、13 mm(M)和35 mm(H)的三种钢纤维,进行单掺、双掺、三掺制备钢纤维增强水泥基材料,采用圆柱体试件进行落锤冲击试验,从冲击次数及耗能、破坏形态、裂缝宽度发展等方面探究混杂方式对水泥基材料抗冲击性能及阻裂能力的影响。试验结果表明:钢纤维从单掺到三掺,材料抗冲击性能逐渐增强。钢纤维单掺对水泥基材料强度及抗冲击性能提升效果依次为:M>H>S;双掺组合方式从优到劣为:M+H>S+M>S+H,当1.5%(体积分数,下同)M与0.5%H混掺时材料的增强、增韧效果最佳,28 d抗折强度为22.6 MPa,较单掺M和H分别提高了3.2%和31.4%,抗压强度为154.8 MPa,较单掺M和H分别提高了40.1%和65.5%,初裂与破坏冲击耗能比单掺M和H分别提高了23.5%、425%和36.7%、300%;三掺最优掺量为0.5%S、0.5%M和1%H,初裂和破坏冲击耗能比最优双掺M1.5H0.5组分别提高了33.3%、1.9%。双参数的Weibull分布可以合理地描述钢纤维混杂增强水泥基材料的初裂冲击次数(N1)和破坏冲击次数(N2)。S抑制微裂缝的产生与扩张,M和H阻止宏观裂缝在不同受荷阶段的发展,在不同结构层次、不同受荷阶段发挥逐级阻裂作用。

激光增材制造沉淀强化镍基高温合金热裂纹研究进展

针对沉淀强化镍基高温合金中的裂纹现象,对比了2类热裂纹(即凝固裂纹和液化裂纹)的典型特征、形成位置和条件。从枝晶生长、元素偏析、强化相析出、固态相变和残余应力应变等角度,系统综述了热裂纹的形成机理和热裂纹敏感性影响因素。在此基础上,从合金成分调控、工艺参数优化、基板预热以及热等静压处理等方面,概述了增材制造高温合金热裂纹调控和抑制的主要措施。最后,针对激光增材制造沉淀强化镍基高温合金热裂纹研究中存在的问题,提出了进一步研究和发展的建议,为实现无裂纹镍基高温合金的增材制造提供了参考。

基于现场湿度和损伤密度的固化土基层疲劳性能仿真

为了有效分析固化土基层在现场湿度分布下的疲劳性能,构建了考虑现场湿度的固化土路面结构数值仿真计算框架。首先基于平衡基质吸力的求解和回弹模量的预估,实现了固化土路面结构内部由于应力依赖和湿敏性引起的材料非线性力学性能的表征;然后基于能量力学法和损伤力学理论构建了非饱和固化土基层疲劳性能仿真理论建模方法;最后利用Comsol Multiphysics软件分析程序中的PDE⁃FE方法实现了在湿度场和应力场耦合作用下的非饱和固化土基层疲劳性能仿真计算。结果表明,该数值仿真计算框架可以较好地实现固化土路面结构的疲劳仿真分析,能够考虑现场湿度分布的影响,从而得到固化土路面结构内部真实力学响应。

氧化损伤对航空发动机涡轮叶片裂纹扩展影响

氧化损伤以及裂纹在涡轮叶片服役过程中不可避免,对裂纹行为的预测及其受氧化损伤的影响对于服役安全和寿命管理具有重要意义。针对航空发动机高压涡轮叶片长期处于高温环境下产生的氧化损伤以及裂纹问题,通过对紧凑拉伸(CT)试样在850℃条件下进行疲劳裂纹扩展试验,得到正常试样和氧化损伤后试样的疲劳裂纹扩展速率;运用Paris模型考虑了存在氧化损伤时裂纹扩展的情况,对比氧化损伤对疲劳裂纹扩展速率的影响。本文以某航空发动机高压涡轮叶片为例,聚焦于氧化损伤对裂纹扩展阶段的影响,利用ANSYS和Franc3D软件分析并对比涡轮叶片在有无氧化损伤条件下的裂纹扩展寿命。结果表明,叶片前缘裂纹受氧化损伤影响下,其循环寿命平均降低到无氧化损伤情况下的44.02%,叶片后缘裂纹循环寿命平均降低到无氧化损伤情况下的50.22%。对实际服役环境工作条件下的涡轮叶片寿命评估提供基础参考,以及在其他实际工程中正确评价材料、预测工程热端零部件的使用寿命和设计强度均有重要的现实意义。