高强度钢管材的喷丸强化研究

研究了超高强度钢圆管件中的疲劳性能与喷丸强化工艺之间的关系。在管壁无氧化的情况下，外壁强化时疲劳裂纹萌生于内壁表面；而当内壁强化时疲劳裂纹则萌生于外壁表面。对内外表现进行强化，可使管材的疲劳极限（Ｎ＝１０＾６）提高４２￣５４％。本文同时还研究了表面强化对旋转弯曲疲劳极限的影响。结果指出，示强化疲劳源位于表面，给出的是材料传统的表面疲劳极限（ＳＦＬ）；而强化后的疲劳裂纹萌生于次表面上，这里获得的为材     

陶瓷喷丸强化对TC4-DT钛合金疲劳性能的影响

为了探讨陶瓷丸喷丸强化对TC4-DT钛合金疲劳行为的影响,对TC4-DT钛合金进行了铸钢喷丸强化和陶瓷喷丸强化,采用表面轮廓仪、扫描电子显微镜、旋转弯曲疲劳、轴向疲劳等研究了2种喷丸介质对TC4-DT钛合金表面粗糙度、表面形貌、表面残余压应力、疲劳寿命、疲劳强度的影响。结果表明:陶瓷丸喷丸对TC4-DT钛合金疲劳极限影响不大,陶瓷丸喷丸后表面形貌和粗糙度明显优于铸钢丸喷丸表面,陶瓷丸喷丸强化效果优于铸钢丸喷丸,可提高疲劳寿命达20倍以上。对于薄壁零件喷丸强化,陶瓷喷丸强度不宜超过0.15 A,喷丸强度过高,强化效果不佳。     

喷丸对扭转疲劳性能的影响EI

对扭转试样进行喷丸和预应变,经强化后试样的对称扭转疲劳极限比磨削态提高20～30％。 断口分析表明,在疲劳极限水平附近运转的扭转疲劳断裂是由正应力引起的,断口与轴线成45°。喷丸试样的硬度分布曲线表明,在表下一定深度存在软化区,而裂纹萌生的位置比软化区更深。 喷丸后扭转疲劳极限提高的主要原因是残余压应力的作用。在喷丸前或后进行预应变均使疲劳极限下降。这和预应变时造成的损伤或在夹杂周围造成裂纹有关,它使疲劳寿命降低。     

不同温度环境下CrMoW转子钢超高周疲劳行为研究

利用旋转弯曲疲劳试验机,研究CrMoW转子钢在常温与600℃条件下的超高周疲劳特性。对试验数据采用三参数模型拟合,用扫描电子显微镜(SEM)对疲劳断口进行分析。研究结果发现,600℃下的S-N曲线呈现直线下降的趋势,不存在传统意义上的疲劳极限。高温会加速试样的氧化,促进裂纹的萌生与扩展,降低材料的疲劳寿命。断口分析表明:疲劳裂纹主要萌生于试样表面,很少发现裂纹萌生于内部的情形。在600℃下,裂纹萌生区普遍发现有夹杂物。对试验前后转子钢硬度值进行测量,没有发生明显变化。     

微粒子喷丸工艺对EA4T车轴钢表面性能和疲劳强度的影响

研究了不同微粒子喷丸工艺对EA4T车轴钢材料表面性能和疲劳强度的影响。基于9种不同喷丸强度或覆盖率(主要由喷丸时间决定)的微粒子喷丸工艺,探究了微粒子喷丸工艺对EA4T车轴钢表面的粗糙度、三维形貌、残余应力、半高宽(FWHM)和表面晶粒尺寸的影响。同时进行疲劳实验得出每种工艺的疲劳极限,并分析了试样断口的形貌。微粒子喷丸在材料表面引入了100μm左右的影响层。随着喷丸强度的增加,材料的表面粗糙度增加。在同一喷丸强度下,20 s喷丸表面粗糙度比10 s与30 s喷丸小。喷丸强度和覆盖率对残余应力最大值的影响较小,但对残余应力层深度的影响显著。喷丸后表面的FWHM最大并在深度方向逐渐减小,喷丸强度越大,喷丸对FWHM的影响层越深。随着喷丸强度和覆盖率的增加,微粒子喷丸试样表面晶粒尺寸减小。所有微粒子喷丸试样疲劳破坏均萌生自表面。不同微粒子喷丸工艺对EA4T车轴钢表面性能的影响不同,但是微粒子喷丸均使材料疲劳极限得到显著提高。     

残余压应力对45钢疲劳裂纹萌生寿命的影响

本文研究了４５钢不同缺口半径及经预压，喷丸处理后对试样弯曲疲劳裂纹萌生寿命的影响。研究结果表明：随着试样缺口根部半径的增大，试样的弯曲疲劳裂纹萌生寿命增加。     

喷丸强化对S280新型超高强度不锈钢疲劳性能的影响

为了研究适宜S280新型超高强度不锈钢的喷丸强化工艺,对S280钢进行不同工艺的喷丸强化,分析了S280钢及其不同工艺喷丸强化后的试样的表面形貌、粗糙度、旋转弯曲疲劳寿命以及疲劳断口形貌,测定了喷丸强化试样的残余应力场.结果表明:喷丸强化后S280钢疲劳寿命有了显著的提高,而大强度的铸钢丸喷丸对其疲劳寿命提高更为有利;喷丸前后的S280钢的疲劳裂纹源均在表面,但喷丸强化使疲劳裂纹由多源变为单源.     

燃机压气机叶片热强钛合金TC11疲劳行为研究

在不同温度对TC11钛合金进行旋转弯曲疲劳性能测试及组织形貌观察,研究了温度对合金疲劳行为的影响。结果表明,在150—250℃,合金的旋转弯曲疲劳强度随着温度的升高而降低。随着温度的升高,合金的屈服与抗拉强度降低,等轴组织的含量也降低,这是合金疲劳强度降低的主要原因。高温下合金的疲劳裂纹从表面萌生,未发现内部萌生的特征。     

8.8级螺栓用ML40Cr钢的疲劳性能和裂纹扩展行为

针对紧固螺栓在不同预紧力下的疲劳可靠性问题,对ML40Cr钢母材进行拉-拉疲劳和对称三点弯曲实验,研究输电铁塔用8.8级紧固螺栓用钢的疲劳性能和裂纹扩展行为。拉-拉疲劳实验的结果表明,在不同应变幅的疲劳加载条件下,以材料抗拉强度的50%作为平均应力时ML40Cr光滑试样的疲劳极限为263 MPa,缺口试样的疲劳极限为95 MPa。用有效应力(σ)参数法处理平均应力对ML40Cr疲劳曲线的影响,得到8.8级螺栓用钢ML40Cr的疲劳缺口敏感度为0.31。依据对称三点弯曲实验的疲劳实验结果,得到8.8级螺栓用钢ML40Cr的裂纹扩展速率关系式为da/d N=10-10(?K)2.2。探讨ML40Cr用钢的缺口疲劳强度和疲劳裂纹扩展机制。     

试样形状尺寸及磨削方法对材料疲劳性能影响的试验研究

目前疲劳试验所使用的试验机类型颇多,试样的形状尺寸和磨削方法也多不一致。为了探讨这些因素对材料疲劳性能的影响,我们进行了试样形状尺寸及磨削方法对材料疲劳性能(主要指旋转弯曲)影响的试验研究。在这方面,国外也有不少报道。由苏联机器制造百科全书中可知,他们的试验结果表明,当应力低于疲劳极限时,试样承受最大应力部分的长度对材料疲劳极限没有影响;当应力高于疲劳极限时,试样形状对疲劳强度有明显的影响,疲劳强度随着最大应力作用部分长度的减小而增     

Influence of surface integrity on fatigue strength of 40CrNi2Si2MoVA steel

Influence of surface integrity (including surface roughness, residual stresses, and microstructure in surface) on fatigue limit of 40CrNi2Si2MoVA steel specimens is investigated comprehensively in this work according to a systematic consideration. The surface integrity of specimens is changed due to several widely used manufacturing procedures: heat-treatment, grinding, electro-polishing, hard chromium plating and shot peening. In comparison with specimen electro-polished after grinding, the specimen without polishing has 10% lower fatigue limit due to higher surface roughness; while shot peening improves the fatigue limit for about 36% due to inducing of compressive residual stress field in the surface and transferring the fatigue crack source from surface to interior. The fatigue limit of specimen with decarburized layer after grinding is lower about 13%, but the shot peening can eliminate its detrimental effect. Hard chromium plating decreases the fatigue limit dramatically. The shot peening carried before plating can improve the fatigue limit of specimen and cause it to get to a level even higher than that of specimen without plating.     

Effects of Shot‐Peening on Fretting Fatigue Crack Growth Behavior in Ti‐6Al‐4V

Abstract: The effects of shot‐peening on fretting fatigue crack growth behaviour in titanium alloy, Ti‐6A1‐4V were investigated. Three shot‐peening intensities: 4A, 7A and 10A were considered. The analysis involved the fracture mechanics and finite element sub‐modelling technique to estimate crack propagation lives. These computations were supplemented with the experimentally measured total fretting fatigue lives of laboratory specimens to assess the crack initiation lives. Shot‐peening has significant effect on the initiation/propagation phases of fretting fatigue cracks; however this effect depends upon the shot‐peening intensity. The ratio of crack initiation and total life increased while the ratio of the crack propagation and total life decreased with an increase of shot‐peening intensity. Effects of residual compressive stress from shot‐peening on the crack growth behaviour were also investigated. The fretting fatigue crack propagation component of the total life with relaxation increased in comparison to its counterpart without relaxation in each shot‐peened intensity case while the initiation component decreased. Improvement in the fretting fatigue life from the shot‐peening and also with an increase in the shot‐peening intensity appears to be not always due to increase in the crack initiation resistance from shot‐peened induced residual compressive stress.     

Effect of shot peening on fatigue limit of surface flawed samples

The effects of shot peening on the fatigue limit of specimens having a semicircular notch of varied surface length, 2a , are investigated. In the case of un-peened specimens, the fatigue limit of specimens having a notch of a = 0.05 mm was equal to that of the un-notched specimens. However, the fatigue limit of a = 0.3 mm was 46% smaller than that of the un-notched specimens. On the contrary, in the case of peened specimens, the fatigue limit of a = 0.2 mm was equal to that of the un-notched specimens and furthermore, that of a = 0.3 mm was only 5% smaller than that of the un-notched specimens. Multiple non-propagating cracks were observed in peened specimens after fatigue testing. The stress intensity factor of the maximum non-propagating crack size corresponded to that of a = 0.2 mm notch. These results indicate that shot peening increases fatigue limit and decreases the likelihood that a surface flaw will result in failure.     

喷丸强化对Ti6Al4V半椭圆表面裂纹J积分和裂纹扩展速率的影响

采用修正的J积分计算方法,考虑残余应力、残余应变和残余应变能,定量计算和分析喷丸强化对半椭圆表面裂纹前沿J积分参数的影响规律。对喷丸强化工艺进行有限元建模仿真,通过改变约束条件生成疲劳裂纹并施加远场载荷,计算J积分和裂纹扩展速率。考虑不同深度的半椭圆表面裂纹和不同丸粒速率对断裂参量的影响。结果表明:丸粒速率一定时,与未喷丸相比喷丸后J积分值的降幅随裂纹深度的增加而减小,喷丸强化有益于抑制疲劳浅裂纹的扩展。当裂纹深度为0.3mm时,裂纹最深点的J积分值由4.25N/mm降低到2.99N/mm,降幅约30.1%。裂纹深度一定时,J积分值随丸粒速率的增大而降低,提高丸粒速率对抑制裂纹扩展更有益。     

IMPROVING THE FATIGUE CRACK RESISTANCE OF WASPALOY BY SHOT PEENING

Four-point bending fatigue tests were conducted to study the effect of shot peening on the fatigue life of the nickel-base superalloy, Waspaloy. The influence of shot peening intensity on crack initiation, Stage I crack growth and the Stage I-to-Stage II crack growth transition phases, has been examined to identify the mechanisms by which shot peening improves fatigue resistance. The potential for extending the fatigue life of fatigue-damaged Waspaloy components has been explored by shot peening specimens which had been cyclic damaged to various degrees. The fatigue test was then continued after peening to ascertain the possibility of crack arrest or extending fatigue life. These experiments explore the possibility of 'healing' fatigue damage by a surface engineering treatment.     

Short‐crack thresholds and propagation in an AISI 4340 steel under the effect of SP residual stresses

The effect of residual stresses induced by shot‐peening in a high‐strength AISI 4340 steel has been studied with the purpose of deriving a consistent fatigue model incorporating the results of fatigue crack growth experiments in the threshold region for a broad range of load ratio (R‐ratio ranging from ?2.5 to 0.7), and the effect of short cracks by means of a modified El‐Haddad model. The proposed model, taking into account the effect of crack closure and being capable to assess the conditions for fatigue propagation of short cracks partially embedded in the shot‐peened surface layer, was validated against constant amplitude fatigue experiments conducted in the endurance strength region, ie, for fatigue lives up to 10⁷ cycles, with micronotched specimens in the presence of shot‐peening residual stresses. The proposed model was also validated by comparing the results of fatigue crack propagation simulations with fatigue crack growth experiments under variable amplitude loading, experimentally reproducing the combined effect of service fatigue loads and shot‐peening residual stresses.     

Einfluß der Oberflächenbeschaffenheit auf die Schwingfestigkeit von Aluminium-Druckguß

Effect of Surface Condition on Fatigue Strength of Die-Cast Aluminium Surface processing like milling or shot peening involves modifications of the surface and subsurface condition of a material that can be described by changes of the residual stresses, the hardness, and the surface roughness. Moreover, there is the possibility of introducing additional surface defects. In this paper the influence of these modifications on the fatigue behaviour of the aluminium die-casting alloy GD-AlSi8Cu3 is presented. S-N curves are determined for four surface conditions produced by milling, shot peening, and a combined treatment. The improvement of fatigue limit by shot peening is confirmed for this material. The additional effect of mean stresses is determined. Investigations of the fatigue fracture surfaces show that pores and pipes as well as surface defects induced by shot peening act as fatigue crack initiation sites.     

Effects of shot-peening intensity on fretting fatigue crack-initiation behaviour of Ti–6Al–4V

The effects of shot‐peening intensity on fretting fatigue crack‐initiation behaviour of titanium alloy, Ti–6Al–4V, were investigated. Three intensities, 4A, 7A and 10A with 100% surface coverage, were employed. The contact geometry involved a cylinder‐on‐flat configuration. Residual stress and improvement in fretting fatigue life were directly related to shot‐peening intensity. The magnitude of compensatory tensile stress and its location away from the contact surface increased with increasing intensity. The relaxation of residual stress occurred during fretting fatigue which increased with increasing the number of cycles. An analysis using a critical plane‐based fatigue crack‐initiation model showed that stress relaxation during the fretting fatigue affects life and location of crack initiation. Greater relaxation of the residual stress caused greater reduction of fatigue life and shifted the location of crack initiation from inside towards the contact surface. Modified shear stress range (MSSR) parameter was able to predict fretting fatigue crack‐initiation location, which agreed with the experimental counterparts. Also, the computed parameter showed an appropriate trend with the experimental observations of the measured fretting fatigue life based on the shot‐peening intensity.     

Influence of residual stresses from shot peening on fretting fatigue crack growth

One method to improve fretting fatigue life is to shot peen the contact surfaces. Experimental fretting life results from specimens in a Titanium alloy with and without shot peened surfaces were evaluated numerically. The residual stresses were measured at different depths below the fretting scar and compared to the corresponding residual stress profile of an unfretted surface. Thus, the amount of stress relaxation during fretting tests was estimated. Elastic–plastic finite element computations showed that stress relaxation was locally more significant than that captured in the measurements. Three different numerical fatigue crack growth models were compared. The best agreement between experimental and numerical fatigue lives for both peened and unpeened specimens was achieved with a parametric fatigue growth procedure that took into consideration the growth behaviour along the whole front of a semi‐elliptical surface crack. Furthermore, the improved fretting fatigue life from shot peening was explained by slower crack growth rates in the shallow surface layer with compressive residual stresses from shot peening. The successful life analyses hinged on three important issues: an accurate residual stress profile, a sufficiently small start crack and a valid crack growth model.     

Initiation and propagation behaviour of fatigue cracks in hard-shot peened Type 316L steel in high cycle fatigue

Observations of fatigue crack growth behaviour were made during rotating‐bend testing of hard‐shot peened Type 316L steel. From the results of these observations, the crack that developed in the axial direction was observed and the mechanism of the fatigue crack properties was clarified as follows: (1) Small circumferential surface fatigue cracks were detected at 60% of the fatigue lifetime. These cracks propagated very slowly in both the circumferential and radial directions. (2) When a radial crack reached a depth of between 150 and 350 μm, axial fatigue cracks were formed. (3) In the next stage, either the radial or the axial fatigue cracks continued propagating, or an inwards growing radial crack formed from the axial crack. (4) In the final stage, the circumferential surface crack began to grow rapidly and resulted in fracture. (5) The fracture type of hard‐shot peened Type 316L is a particular type of surface fracture.