一种[001]取向镍基单晶高温合金蠕变特征

研究了一种[001]取向镍基单晶合金的蠕变特征和变形期间的微观组织结构.结果表明:在低温高应力和高温低应力条件下,合金具有较长的蠕变寿命和较低的稳态蠕变速率;在700℃,720MPa条件下,透射电镜(TEM)观察显示蠕变期间的变形特征是12<110>位错在基体中运动,发生反应形成13<112>超肖克利(Shockley)不全位错,切入γ′相后产生层错.在900℃,450MPa条件下,没有出现蠕变初始阶段,γ′相从立方体形态演化成筏形;在加速蠕变阶段,多系滑移开动,大量位错剪切γ′相是变形的主要机制.在1070℃,150MPa条件下,γ′相逐渐转变成筏形组织,并在γ/γ′界面处形成致密的六边形位错网,位错网可以阻止位错切入γ′相,提高蠕变抗力;在蠕变后期,位错以位错对形式切入γ′相,是合金变形的主要方式.     

晶体取向对镍基单晶DD6合金蠕变性能的影响

针对航空发动机镍基单晶涡轮叶片高温服役下蠕变寿命的取向敏感性难题，开展了DD6单晶合金［001］、［011］与［111］3种典型取向在980^oC下的蠕变试验，获得了服役温度下单晶合金的蠕变寿命、伸长率，均为［111］取向>［001］取向>［011］取向；通过对蠕变过程中微观组织演化以及蠕变断裂后断口形貌进行分析，揭示了不同取向下单晶合金的蠕变失效机理；基于晶体塑性理论，建立了DD6单晶考虑取向敏感性的粘塑性本构及损伤方程，能够较好地拟合不同晶体取向单晶的蠕变过程，为单晶叶片的强度分析与寿命预测提供参考。     

Ti-55511合金高温蠕变行为TEM分析

文章结合Ti-55511钛合金的高温工作环境进行了4组蠕变实验：400℃200MPa、400℃300MPa、500℃200MPa以及500℃300MPa。蠕变后,使用透射电镜实验观察了蠕变后样品的微观组织。结果表明：高温高应力状态下,位错攀移在蠕变过程中占主导地位;在高温低应力或低温高应力状态下,合金蠕变过程主导机制为位错滑移;当温度较低,应力相对较低时,合金蠕变过程中主导机制为晶界扩散机制。     

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=30MPa·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.     

Effect of Columnar Crystals on Fatigue-Creep Failure Behaviour of Fe-Ni-Cr Alloy

研究了在交变应力与平均应力迭加条件下，柱状晶体对铁镍铬金的疲劳－蠕变失效行为的影响，结果表明，疲劳－蠕变应力迭加对合金产生交互作用，使其循环断裂寿命大大降低．具有横向柱晶界的试样受到了最强烈的交互作用．断口形貌观察揭示了沿柱晶界脆断是具有横向晶界试样的主要疲劳－蠕变断裂机理．而沿柱晶界断裂附带塑性撕裂结构以及二次裂纹形成所表示的脆－塑性断裂相混合的机理是其它取向试样的主要断裂机理沿柱晶界分布的脆性夹杂物引发沿晶微裂纹并加速沿晶界扩展     

掺杂钨带退火过程中的组织与织构演变

对掺杂钨带在1 000～1 500℃等温退火过程中的组织与织构变化进行研究.研究结果表明:未退火钨带为拉长的纤维组织,纤维宽窄不一,纤维内部存在长短不一的条形胞.于1 200℃,1h条件下退火时由于亚晶长大发生纤维宽化与纤维界的锯齿化,但无再结晶晶粒形成.当退火温度升高至1 400℃时,纤维界处出现细小的等轴状再结晶晶粒,这些再结晶晶粒的形成机制是亚晶转动.1 500℃退火后,再结晶晶粒增多,但长大不明显,这主要是由于K泡对亚晶界或位错的钉扎作用,使亚晶转动与亚晶界迁移受到阻碍,延缓了再结晶形核与核心长大.拉拔钨丝织构为[110]丝织构,钨丝轧制为钨带后,[110]丝织构转变为{001}＜110＞和{111｝＜110＞织构,1 500℃退火后,亚晶转动使钨带织构转变为沿α取向线均匀分布的{uvw}＜110＞织构,与拉拔钨丝的[110]丝织构类似.     

高温环境2A12–T4铝合金多轴疲劳失效规律研究

许多工程结构在服役过程中往往承受着复杂的多轴疲劳载荷和热力耦合作用,仅靠常温情况下的单周载荷来简化复杂多轴载荷状态的失效预测方法将不再适用。为研究2A12–T4铝合金的高温多轴疲劳失效规律,本实验在175℃环境温度下,选取等效Von-Mise应力幅值,通过间断式加载记录不同拉扭加载循环下的裂纹萌生与扩展情况,研究特定加载路径对裂纹萌生与扩展的影响。实验结果表明,相位差为0时,裂纹萌生方向沿MSSA平面;在相位差为45°时,裂纹萌生传播方向与最大切应力平面方向相近,最大切应力在裂纹萌生过程中起到主要作用;在λ=0.5、φ=0和λ=1.0、φ=0两种情况下,裂纹萌生初期沿着最大切应力平面方向传播,传播过程中存在第I阶段向第II阶段转变的过程;在λ=0.5、φ=45°和λ=1.0、φ=45°两种情况下,不存在明显的第I阶段向第II阶段转变的过程;对比4种加载方式下的疲劳裂纹萌生期与疲劳寿命比,发现切应力比重的增大加速裂纹的萌生过程,相位差的存在阻碍了裂纹的萌生过程。     

定向凝固对一种高强度铸造镍基高温合金的组织和性能的影响

研究了定向凝固对一种高强度铸造镍基高温合金的组织和性能的影响,发现合金的低倍和显微组织与定向凝固速度以及凝固后的冷却速度密切有关。定向凝固可大幅度地提高合金的塑性、热疲劳性能和中温持久性能,使瞬时拉伸及高温持久性能也有显著改善。中温(～760℃)持久寿命的提高主要是由于蠕变第二阶段的延长,而高温(～980℃)持久寿命的提高主要是由于蠕变第三阶段延长的结果。通过定向凝固改善高强度铸造镍基高温合金的高温机械性能的主要原因是消除了垂直于应力轴的横向晶界;另一个原因是获得[001]方向择优生长的柱状晶。高温固溶热处理可降低第二阶段的蠕变速度,延长蠕变第二阶段,从而进一步大幅度提高中温持久寿命,这主要是由于冷却析出的细小γ′相代替了铸态粗大γ′相的缘故。定向凝固及高温固溶热处理可提高合金的中温(～760℃)持久寿命和延伸率达3-4倍、热疲劳性能达5倍左右。消除了横向晶界的定向凝固合金中,初生MC是蠕变裂纹及热疲劳裂纹的策源地,预计降低合金的碳含量从而减少MC数量将进一步改善合金的高温机械性能。     

热机械循环迭加对断裂寿命及断裂行为的影响

在分析热机械疲劳应力状态基础上，测定了热机械疲劳断裂寿命曲线，并研究了断裂特征行为对热机械循环迭加方式的依赖关系．蠕变裂纹萌生与疲劳裂纹扩展是在具有大应变幅的反相迭加（Ｏｕｔ０６ｐｈａｓｅ）条件下试样断裂主要机制．降低热循环范围的最低温度导致疲劳裂纹萌生及扩展，从而加速了穿晶疲劳断裂过程，降低了断裂寿命．晶界上分布的非金属夹杂物诱发沿晶开裂，但晶内夹杂物对穿晶裂纹扩展过程影响不大．减少或消除非金属夹杂物含量有益于提高工程合金断裂抗力．     

交变载荷与温度耦合对γ-TiAl合金疲劳裂纹扩展影响研究

利用分子动力学方法，在交变载荷与温度耦合条件下，模拟γ-TiAl合金的疲劳裂纹演化过程，探索TiAl合金不同阶段疲劳性能变化的微观机理，得到了在周期循环拉压加载时间比R=10∶1，沿[001]方向以v=10 m/s恒定速率交变加载时，不同温度（300 K、750 K、950 K）条件下，单晶TiAl合金疲劳断裂及缺陷演化的规律。结果表明：交变载荷与温度耦合加载时，在同一应力条件下，随温度的升高，发射位错数量增加且衍生多种类别缺陷，系统初始开裂应变量增大，位错的演化使应力-应变关系发生波动现象。位错密度峰值多集中于应力峰值区域，位错演化与产生的体心立方结构、面心立方结构衍生过程有关。该研究成果为复杂外载荷状态及不同温度条件下的γ-TiAl合金性能设计提供有力的理论指导。     

Deformation and damage features of a Re/Ru-containing single crystal nickel base superalloy during creep at elevated temperature

The deformation and damage features of a 4.5%Re/3.0%Ru-containing single crystal nickel-based superalloy during the creep in the temperature range of 1040–1070 °C and stress range of 137–180 MPa was investigated by means of creep properties measurement and contrast analysis of dislocation configuration. The results showed that the alloy exhibited a better creep resistance in the range of the testing temperatures and stresses, the deformation mechanism of the alloy during steady state creep was dislocations climbing over the rafted γ′ phase.In the latter period of creep, the deformation mechanism of the alloy was dislocations shearing into the rafted γ′phase. It is believed that the dislocations shearing into γ′ phase may cross-slip from {111} to {100} planes for forming the K-W locks to restrain the slipping and cross-slipping of dislocations on {111} plane. As the creep goes on, the alternate slipping of dislocations results in the twisted of the rafted γ′ phase to promote the initiation and propagation of cracks along the γ/γ′ interfaces up to creep fracture, which is considered to be the damage and fracture feature of alloy during creep at high temperature.     

Influence of γ' precipitate on deformation and fracture during creep in PM nickel-based superalloy

FGH96 is a powder metallurgy nickel based superally used for turbine disk of aero-engines. In the present study FGH96 alloy with four different γ' precipitate microstructures were produced via solution heat-treatment with different cooling rates, and the maximum cooling rate reached 400°C/min which was a super cooling rate for Nickel-based superalloy. The creep tests were conducted for PM FGH96 alloy under the testing condition of 704°C and 690 MPa. The relationship between the creep properties and the distribution of γ' precipitate was established. The creep mechanism was analyzed by using TEM and ACTEM, and the dislocation movement was studied at the atomic scale. The creep strain rate was calculated through a physically based crystal slip model established based on crystal plasticity. The calculated results were consistent with the test ones, illustrating the validity of the model. The fracture mechanism was also investigated, and the results showed that the creep cracks generated on the surface due to the oxidation. It was observed that the cracks propagated in different ways depending on the different average diameters of γ' precipitate. With the decrease of the average γ' precipitate size,the critical shearing stress increased and the resistance of the dislocation slipping increased. The fracture mechanism for the primary stage transformed from intragranular to intergranular due to the change of dislocation slipping.     

应力梯形波加载下的循环蠕变曲线函数

为了确定循环蠕变应变与有载时间的函数关系式,通过对高温合金蠕变试验曲线的分析,发现静蠕变寿命分数曲线遵循与加载应力的大小无关,与循环蠕变寿命分数曲线基本重合的规律,这规律显示了材料本身的蠕变特性。由这规律导出了静蠕变应变与循环蠕变应变之间的关系式,找到了由静蠕变函数确定循环蠕变函数的方法,该方法得到了DZ417G高温合金钢在870oC、梯形应力波加载下蠕变实验数据的支持。     

Finite Eement Facture Aalysis of the Main Arm of Tower Cranes with the 3-D Cracks

In this paper the local solutions of displacement fields in front of three-dimensional cracks are introduced and a new singular element of three-dimensional crack problems is constructed, and a new method for calculating stress intensity factors of three-dimensional crack problems is presented. With the present method, the structural strength of with longitudinal closed cracks under axial tensions is analyzed. It is possible for the crack to propagate because there are ring tensile stresses near joints of the main arm in tower cranes under axial press stresses. The stress and the stress intensity factor are calculated at joints on the main arm of tower cranes. Influences of welding residual stress on stress intensity factors and stresses are discussed.     

固溶热处理对一种第三代镍基单晶高温合金组织及高温持久性能的影响

研究了固溶热处理对一种Re含量为6.5%(质量分数)的第三代单晶高温合金组织及持久性能的影响,实验结果表明:合金铸态下存在明显的凝固偏析,枝晶间区域存在大量的(γ+γ′)共晶组织。固溶过程中,共晶组织在1 335℃以上开始快速溶解,但难熔元素,尤其是Re元素的偏析需要在1 360℃以上才能有明显改善;经过1 365℃固溶后疏松含量增加至0.21%(体积分数),接近铸态下疏松含量的5.2倍。铸态及经1 360℃和1 365℃固溶热处理后合金的持久性能测试结果显示:固溶热处理显著改善了合金的持久性能,且固溶温度越高,持久性能越高。在高温持久加载过程中,铸态合金的裂纹主要沿枝晶间分布,在(γ+γ′)共晶组织处萌生;当固溶温度较低时,且枝晶干处析出了较多的TCP(topologically close-packed)相,未能充分降低Re元素的偏析可能是导致枝晶干处TCP相大量析出的主要原因;当固溶温度较高时,TCP相析出量较少。     

冷却速度对圆形加载路径下A319铝合金多轴疲劳特性的影响

采用MTS809型电液伺服疲劳试验机、扫描电镜研究了不同冷却速度对A319铝合金圆形加载路径下的疲劳特性.结果表明:当冷速为10℃·s-1时,材料中二次枝晶臂间距、硅颗粒及孔洞尺寸较冷速为0.1℃·s-1时要小.二次枝晶臂间距较小时,滞后回线面积小,材料应力应变近乎同相,且附加强化效果明显.不同冷速条件下裂纹萌生位置不同,在冷速为10℃·s-1的材料中,裂纹在大硅颗粒处萌生,随着冷速降低至0.1℃·s-1时,裂纹位于孔洞处萌生.对于A319铸造铝合金来说,冷速的变化对其轴向与切向循环特性并无直接影响,轴向表现为先硬化再软化,切向表现为先硬化后稳定的趋势.     

岩石单轴压缩下破坏失稳过程SEM即时研究

通过在扫描电镜下进行单轴加载实验,即时观察分析岩石受力过程中微裂纹的萌生、扩展和贯通破坏的全过程,得到各试样的应力 应变曲线及其所对应的微结构变化的电镜照片·实验结果表明,岩石试件的变形与破坏过程可以分为裂纹压密、微裂纹萌生和扩展以及断裂破坏３个阶段;微裂缝首先在预裂缝周围的拉应力集中区产生,随着外载荷的增加不断扩展,最后形成与最大主应力方向平行的宏观断裂带·     

GH132合金盘材缺口对疲劳及蠕变/疲劳交互作用下的力学性能的影响

GH_(132)合金虽不具有持久缺口敏感性,但仍存在着低周疲劳的缺口敏感。蠕变/疲劳交互作用的断裂寿命曲线,无论是光滑还是缺口都具有一个最大值的“鼻子曲线”。在“鼻子”的上部合金存在缺口敏感性,而在“鼻子”的下部和“鼻子”区域,缺口试样寿命高于光滑试样寿命。本文提出涡轮盘材料的发展应在提高强度的同时,不断改善塑性,以达到“强韧化”的效果。     

Deformation and damage behaviors of as-cast TiAl-Nb alloy during creep

By means of creep properties measurement and microstructure observation,the deformation and damage behavior of an as-cast TiAl-Nb alloy during creep at temperature near 750°C were investigated.The results showed that the microstructure of the alloy consisted of lamellarγ/α_2 phase,and the boundaries consisted ofγphase located in between lamellarγ/α_2 phases with different orientations.In the latter stage of creep,the dislocation networks appeared in the interfaces of lamellarγ/α_2 phases due to the coarsening of them,which made the coherent interface transforming into the semi-coherent one for reducing its adhesive strength.The deformation mechanism of the alloy during creep was twinning and dislocations slipping within lamellarγ/α_2 phases.In the later period of creep,significant amount of dislocations plied up in the interfaces of lamellarγ/α_2 phases,which may cause the stress concentration to promote the initiation and propagation of the cracks along the lamellarγ/α_2interfaces perpendicular to the stress axis.Wherein,some cracks on the various cross-sections were connected by tearing edge along the direction of maximum shear stress,up to the creep fracture,which is considered to be the damage and fracture mechanism of alloy during creep at 750°C.     

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.