GH2036高温合金激光冲击强化后的残余应力

采用X射线衍射仪和材料试验机对激光冲击强化GH2036高温铁基合金的残余应力进行了研究.结果表明,激光诱导GH2036高温铁基合金的残余应力值和残余压应力层的深度随激光功率密度的增加而增加.激光强化件形成的残余应力在高温回火后有所松弛,但仍然保持较高的残余应力水平,一次回火后表面残余应力在-170 MPa,二次回火后残余应力仍然保持在-135 MPa.激光冲击强化件的疲劳寿命比未强化件的提高2.36倍以上.     

激光冲击与喷丸复合强化TC17钛合金表层残余应力研究

目的 分析激光冲击与机械喷丸复合强化钛合金表层残余应力场及其在疲劳载荷下的稳定性。方法 采用薄壁叶片强化参数先后对TC17钛合金表面进行激光冲击强化和喷丸强化,利用X射线衍射法分析两种工艺复合强化表层的残余应力分布,并分别在25、400 ℃拉-拉疲劳加载条件下分析复合强化表层残余应力的稳定性。结果 激光冲击与喷丸复合强化表面残余应力值为-600 ~ -800 MPa,残余压应力幅值沿深度不断递减,压应力层深度为0.7~0.8 mm。表面至0.1 mm深度范围内的残余应力分布梯度较大,其分布特征主要受控于喷丸工艺,而距表面0.1 mm以下的残余应力分布梯度较小,其分布特征受控于激光冲击强化工艺。结论 激光冲击和喷丸强化顺序对最表层残余应力的均匀性有一定影响,对最表层以下的残余应力分布影响较小。复合强化表面残余应力在室温疲劳加载后具有较好的稳定性,在400 ℃疲劳加载下发生一定量松弛后趋于稳定。     

TC4钛合金激光冲击强化与喷丸强化的残余应力模拟分析

目的 通过对激光冲击强化和喷丸强化后的试样进行残余应力测试分析,得出两种工艺在残余应力形成机理、残余应力层深以及残余应力均匀性等方面的差异.方法 一方面采用有限元方法 模拟激光冲击强化及喷丸强化的过程,将材料在两种强化冲击下的响应进行对比,研究残余应力的形成过程,并对残余应力场的分布规律进行总结分析.另一方面,分别用两种强化技术处理TC4钛合金的表面,并用剥层X射线衍射实验测试材料表层的残余应力.最后将实验结果 与测试结果 进行对比,验证有限元模拟的有效性.结果 当这两种强化效果产生-500 MPa的表面平均残余应力时,激光冲击强化后的TC4钛合金表层残余压应力层深度可达0.6 mm以上,而喷丸强化后的TC4钛合金表层残余压应力层深度只有0.15 mm左右.结论 由于诱发材料塑性变形的机制不同,激光冲击强化往往能获得比喷丸强化更好的残余压应力深度,同时激光冲击强化的材料的表面残余应力分布也比喷丸强化的材料更均匀.     

2A12铝合金激光冲击强化残余应力松弛特性

对2A12铝合金试件引入激光冲击强化工艺,借助无损应力测试与三坐标测试技术分析试件表面残余应力场与表面形变量的分布特点,并研究应力循环下的残余应力松弛特性。结果表明,激光能量越大,则引入的残余应力水平越高、表面形变量越大,影响程度呈现出中心大边缘小的特点。应力循环载荷下该残余应力易发生松弛,尤其在第一次循环周期内应力松弛量超过一半,且对应力幅、应力比敏感。     

激光冲击强化与喷丸强化对FGH97高温合金疲劳性能的影响

对FGH97粉末高温合金进行激光冲击强化和喷丸强化,利用X射线应力分析仪测定强化层的残余应力,测定650℃下旋转弯曲疲劳性能,利用SEM观察分析疲劳断口特征。 结果表明,2种表面强化方法都可以提高FGH97粉末高温合金的疲劳性能,但激光冲击强化试样比喷丸强化试样具有更深的残余压应力层和较好的表面粗糙度,且残余应力在高温疲劳载荷下的松弛较小,因此具有更好的强化效果;与未表面强化的试样相比,喷丸强化试样和激光冲击强化试样的疲劳裂纹源都出现在亚表面,而未强化试样的疲劳裂纹源则出现在表面。     

激光冲击强化TC17钛合金室温和高温拉伸性能研究

目的分析激光冲击强化对钛合金室温和高温拉伸性能的影响。方法用YAG纳秒脉冲激光器对TC17钛合金板状拉伸试样表面进行双面激光冲击强化,脉冲能量为25 J,脉冲宽度为15 ns,光斑尺寸为4.2 mm×4.2 mm,搭接率为10%,强化1次。通过室温及400℃下拉伸试验,获得强化前后试样的抗拉强度、屈服强度和断裂伸长率,利用X射线衍射法测试拉伸前后试样表面的残余应力,并在扫描电镜下观察拉伸试样断口微观形貌。结果室温拉伸试验时,激光冲击强化对TC17钛合金的室温抗拉强度和伸长率几乎无影响,但强化后的室温屈服强度下降约6.1%,有/无强化试样均没有明显的屈服点,距离强化试样断裂位置10 mm的表面残余压应力较拉伸前下降约12%。400℃拉伸试验时,激光冲击对TC17钛合金的高温抗拉强度和屈服强度均影响较小,有/无强化试样均出现明显的屈服点,距离强化试样断裂位置10 mm的表面残余压应力较拉伸前下降约44%。结论激光冲击强化在TC17钛合金表面引入显著的残余压应力分布,对屈服强度具有一定程度的影响。强化后试样的屈服强度与拉伸过程中残余压应力松弛速率有关,室温拉伸过程的残余应力松弛较高温拉伸过程慢,试样内部的平衡拉应力区更容易先发生屈服。这是造成室温拉伸屈服强度小幅降低的主要原因。     

激光冲击强化和喷丸强化对FGH97高温合金疲劳性能的影响

对FGH97粉末高温合金进行激光冲击强化和喷丸强化,利用X射线应力分析仪测定强化层的残余应力,测定650℃下旋转弯曲疲劳性能,利用SEM观察分析疲劳断口特征。结果表明,2种表面强化方法都可以提高FGH97粉末高温合金的疲劳性能,但激光冲击强化比喷丸强化具有更深的残余压应力层和较好的表面粗糙度,且残余应力在高温疲劳载荷下的松弛较小,因此具有更好的强化效果;与未表面强化的试样相比,喷丸强化和激光冲击强化试样的疲劳裂纹源都出现在亚表面,而未强化试样的疲劳裂纹源则出现在表面。     

激光冲击强化对AISI202不锈钢焊接接头残余应力的影响

采用两种冲击方式对AISI202不锈钢焊接接头表面进行激光冲击强化处理,利用X射线应力仪测试了激光冲击强化处理后焊接接头的残余应力,研究了单面和双面激光冲击对残余应力分布的影响,分析了残余压应力的形成机理。结果表明,双面激光冲击强化处理效果明显优于单面冲击方式,双面冲击方式能够使试样正反面都获得很大的残余压应力,并且反面的残余压应力水平高于正面,同时使得正反两面残余压应力分布趋于均匀。     

激光冲击强化残余应力场的数值仿真分析

基于激光冲击强化LY12CZ航空铝合金的试验,采用显式动力学有限元软件ANSYS/LS-DYNA对激光冲击诱发的残余应力场进行数值模拟。对模拟中的关键问题,如加载历史、本构关系、网格划分、求解时间等进行了处理。对激光冲击强化后,冲击区表面和深度方向上的残余应力分布特点进行了分析。研究表明,在最佳激光峰值压力下, LY12CZ航空铝合金经激光冲击后,金属表面产生深度为0.5 mm的残余压应力。模拟和试验结果相比,分布规律具有一致性,最大残余应力相差10.2 %。获得的结果将为激光冲击强化过程的控制,和进一步的实验研究提供理论依据。     

激光冲击诱导的残余应力洞数值建模仿真分析

通过建立ANSYS/LS-DYNA有限元仿真模型,对激光冲击处理后靶材的残余应力场进行了有效的预测,对隐式分析前后模型的表面形貌进行了分析,对不同激光冲击参数下激光冲击强化产生的残余应力洞进行了分析。结果表明,增加峰值压力、冲击次数和光斑直径虽然可以改善激光冲击强化效果,增加最大残余应力,但同时也会增大残余应力洞现象,使用方形光斑可以有效减弱残余应力洞现象。     

Relaxation of residual stresses in 20%SiC_w/6061Al composite as-extruded at high temperature

1　ＩＮＴＲＯＤＵＣＴＩＯＮＡｌｕｍｉｎｕｍｍａｔｒｉｘｃｏｍｐｏｓｉｔｅｒｅｉｎｆｏｒｃｅｄｗｉｔｈｓｉｌｉ ｃｏｎｃａｒｂｉｄｅｗｈｉｓｋｅｒ (ＳｉＣｗ/Ａｌ)ａｓａｎｅｗｔｙｐｅｏｆｓｔｒｕｃｔｕｒａｌｍａｔｅｒｉａｌｎｏｔｏｎｌｙｈａｓｃｅｒｔａｉｎａｄｖａｎｔａｇｅｓｓｕｃｈａｓｈｉｇｈｓｐｅｃｉｆｉｃｓｔｒｅｎｇｔｈ ,ｈｉｇｈｓｐｅｃｉｆｉｃｍｏｄｕｌｕｓ ,ｌｏｗｃｏｅｆｆｉｃｉｅｎｔｏｆｔｈｅｒｍａｌｅｘｐａｎｓｉｏｎ (ＣＴＥ)ａｎｄｓｏｏｎ ,ｂｕｔａｌｓｏｃａｎｂｅｓｅｃｏｎｄａｒｉ…     

Ti-4Al-1.5Mn合金高温应力松弛本构模型及应用验证

研究了Ti-4Al-1.5Mn合金在500~700℃的应力松弛特性,首先在蠕变试验机上开展了该合金500、600和700℃条件下的松弛试验,基于松弛数据分别建了双曲正弦和时间硬化两类本构模型,并对模型的预测精度进行了预测。随后把2类本构模型应用于ABAQUS软件对板材V形弯曲过程进行了仿真分析。结果表明,应力松弛的影响因素主要有温度和时间,松弛过程可以分为2个阶段,第1阶段应力快速下降,第2阶段缓慢下降并逐渐稳定于松弛极限。双曲正弦和时间硬化模型均可以对松弛过程进行较准确地预测,V形弯曲后回弹结果表明双曲正弦比时间硬化模型具有更高的预测精度。研究结果对利用应力松弛进行精确成形的工艺设计具有指导意义。     

BT20钛合金高温应力松弛行为研究

通过高温应力松弛实验对BT20钛合金在700～850℃,不同初应力条件下短时应力松弛行为进行研究。结果表明:随着温度升高,BT20钛合金应力松弛速率加快,但长时间应力松弛后剩余应力趋向于一极限值。相同温度下,不同初应力作用的应力松弛极限相同。     

Modeling of Residual Stress in Oxide Scales

The magnitude of the residual stress in an oxidescale, and how this varies with temperature, is of majorimportance in understanding the failure mechanisms ofoxide scales. This stress encompasses both growth stresses introduced at the oxidationtemperature and thermal-expansion-mismatch stressesinduced on heating and cooling, as well as anyexternally applied stresses or stress relaxation whichtakes place in the scale/substrate system. Althoughsome of these components are reasonably well understood(e.g., thermal stresses), growth stresses and therelaxation of the total scale stress by creep orfracture processes are much less well understood. Inthis study a model has been developed to predict stressgeneration and relaxation in oxide scales as a functionof time and temperature for both isothermal exposure and cooling to room temperature. The modeldetermines growth stress and thermal-stress generationin the scale and how this is balanced by stresses in thesubstrate. The substrate stresses are then allowed to relax by creep and the scale stressesrecalculated. This model accurately predicts theroom-temperature scale stresses for a range ofscale/alloy systems. The model can be used to show howthe scale stress depends on oxidation temperature,cooling rate, substrate, and scale thickness. The modelpredictions are discussed in light of experimentalobservations for alumina scales on FeCrAlY.     

Nanoparticulate origin of intrinsic residual stress in thin films

The formation of grains in thin films generates intrinsic residual stress. In this work, we present a model of intrinsic residual stress calculation based on the size-dependent phase transitions of the nanograins. Evaporated thin films are produced by condensation from the vapor on the substrate. It is assumed that the starting nanograins grow from the liquid phase. It is well established that the melting temperature of nanoparticles is a function of their size. By assuming that the intrinsic stress originates from the volume change of the nanograins, and taking into account relaxation processes, the generated intrinsic residual stress in the films is evaluated. The results of the model are compared quantitatively with experimental data obtained from Ta, Mo, Pd and Al films deposited on Si. This model also gives a theoretical interpretation of Thornton and Hoffman’s modelling of the stress-temperature diagram of thin films.     

Residual Stress Relaxation of Shot-Peened Deformation Surface Layer on Duplex Stainless Steel Under Applied Loading

The relaxation of residual stress in shot-peened surface layer of duplex stainless steel S32205 under static and cyclic loading was investigated. The results reveal that the compressive residual stress is relaxed under applied tensile stress. The relaxation of residual stress in longitudinal direction is more obvious than that in transverse direction in both austenite and ferrite. When the applied stress is beyond the yield strength of the materials, the relaxation of the residual stress becomes drastic. Under cyclic loading, the residual stress relaxation occurs fast in the first few cycles, it then becomes stable gradually. A model was used to quantitatively calculate the residual stress under cyclic loading with different applied tensile stresses. The relaxation behavior is determined by the applied loading, the number of cycles, dislocation density, and the residual stress gradient. The relaxation behavior difference under cyclic loading between ferrite and austenite is discussed.     

不锈钢板翅结构钎焊残余应力及其高温蠕变松弛行为三维有限元分析

利用有限元软件ABAQUS,对不锈钢板翅结构在钎焊过程中产生的残余应力及其高温下的蠕变松弛行为进行三维有限元分析,得到了残余应力的变化规律.结果表明,由于镍基钎料BNi-2和不锈钢母材304力学性能的差异以及夹具的约束作用,钎焊后在接头处产生了较大的残余应力.在高温环境下,由于蠕变松弛,残余应力大幅度下降.在蠕变稳态阶段,钎缝处仍然存在一定的残余应力;钎角处蠕变应力和应变集中,易萌生裂纹,成为最薄弱环节.研究结果为板翅结构的高温强度设计提供参考.     

Residual Stress Modeling in Orthogonal Machining

A predictive model for residual stresses in orthogonal cutting is presented. It uses process conditions as inputs and predicts surface and sub-surface residual stress profiles due to machining. The model formulation incorporates cutting force and cutting temperature predictions and utilizes those parameters to define the thermo-mechanical loading experienced by the workpiece. The stresses at the cutter edge hone and in the shear plane are considered in a rolling/sliding contact algorithm which admits kinematic hardening for non-proportional plasticity with subsequent stress relaxation to meet boundary conditions. Model predictions are compared to experimentally-measured residual stresses under various cutting conditions for validation.     

材料复杂残余应力的高温松弛行为

介绍了材料表面应力状态的X射线测量方法，研究了低碳钢交叉焊缝残余应力状态及其热松弛行为。结果表明，焊缝表面残余应力状态比较复杂，加热处理不但可有效降低应力幅度，对应力状态也产生一定影响。加热温度及时问是决定应力松弛的关键因素。在加热退火期间，Mises等效残余应力按幂指数方式松弛．并遵循蠕变机制。     

Thermal Relaxation of Residual Stresses in Shot Peened Surface Layer of SiCw/Al Composite

The residual stress relaxation of the shot peened layer on the SiCw/Al composite during isothermal annealing was investigated. The results showed that the residual stresses relaxed in the whole deformation layer especially when the annealing temperature was higher than 200?°C. The relaxation process during isothermal annealing could be described precisely using Zener-Wert-Avrami function. Because of high intensity dislocation around reinforcements producing a large amount of stored energy, the residual stress relaxation activation enthalpy of shot peened SiCw/Al was smaller than self-diffusion activation enthalpy of pure aluminum. According to the analysis of full-width at half-maximum (FWHM) of the shot peened composite in different annealing temperatures, it can be concluded the recovery and recrystallization behavior became intensely when anneal temperature was larger than 200?°C. The small relaxation of residual stress in low annealing temperature was mainly due to partly recovery and recrystallization in a very low level.