共查询到19条相似文献,搜索用时 140 毫秒
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针对老龄飞机7150铝合金结构普遍存在的剥蚀问题,在海洋性盐雾环境下,通过T73时效态不受载和悬臂梁加载剥蚀试验,以及T77时效态波音737CL龙骨梁下缘条不受载和受载剥蚀试验,研究了正应力对7150铝合金剥蚀的影响。结果表明:T73时效态剥蚀,L轴向拉应力作用表面最轻,其次为不受载表面,L轴向压应力作用表面最严重。T77时效态龙骨梁下缘条剥蚀,在L轴向压应力作用下的产生和扩展速度,比不受载状态下快得多。由此认为:L轴向压应力可以加速7150铝合金剥蚀的形成和扩展,而L轴向拉应力可以抑制剥蚀的形成和扩展。 相似文献
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采用压痕应变法测量2219-T87高强铝合金FSW试板与筒体结构上典型位置的残余应力. 结果表明,在试板上接头残余应力呈不对称分布,焊缝上的纵向残余应力数值高于横向残余应力,纵向应力的最大拉应力出现在焊缝中心位置,最大压应力出现在后退侧轴肩外侧,横向残余应力的最大压应力出现在前进侧轴肩边缘;筒体结构的环缝上,纵向残余应力呈较大拉应力,横向残余应力的数值较小,纵缝接头处残余应力关于焊缝中心呈对称分布,纵向残余应力在焊缝上呈拉应力,横向残余应力在焊缝上呈压应力;压力试验使结构件上部分应力释放,应力数值略有下降. 相似文献
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高强度钢压剪疲劳裂纹扩展的实验研究 总被引:1,自引:1,他引:0
滚珠轴承接触点附近的高压剪应力是引起轴承疲劳破坏的原因。为获得高强度钢在压剪疲劳加载下的断裂性态,通过轴向裂纹薄壁圆筒的压剪疲劳加载试验,研究了这类材料的疲劳破坏规律。结果表明,复合疲劳加载时门槛值对压应力分量并不敏感,但对扩散速率和临界扩展角却有明显影响。裂纹扩展速率随压应力增加而提高,裂纹较快达到失稳;裂纹扩散角则随压应力增加而减小,疲劳裂纹将向有利于Ⅰ型断裂的方向扩展。这表明轴承滚道内,任何平行于压应力的缺陷、微裂纹都将是十分危险的。 相似文献
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采用盲孔法和压痕法,分别对2195-F态铝锂合金手工TIG焊和FSW焊后残余应力进行测量. 结果表明,盲孔法的测量值普遍高于压痕法. 两种焊接方法,近焊缝区的纵向应力均高于横向应力;横向应力整体表现为压应力或小于50 MPa的拉应力;纵向应力在热影响区附近表现为大于焊缝的拉应力. 焊缝区附近,手工TIG焊纵向残余应力大于FSW,且纵向残余应力表现为较大的拉应力,最大值接近于接头的屈服强度;焊缝区外,手工TIG焊和FSW残余应力值相差不大,其横向残余应力基本表现为很小的拉应力或者压应力. 相似文献
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采用电子束焊接TA12钛合金薄板焊缝表面成形良好,焊缝区以马氏体组织为主,细小的稀土相呈均匀弥散分布状态;随着距焊缝距离的增加,稀土相尺寸逐渐增大,数量逐渐减少,并逐渐趋于球形,沿接头呈一定的规律性分布.小孔法残余应力测试结果表明,垂直于焊缝方向残余应力以纵向应力主,应力呈梯度分布,横向应力较低;焊缝区为纵向拉应力区,应力峰值低于其屈服强度,横向应力为较小的压应力;沿焊缝试板中心区(±20 mm范围内)焊接残余应力分布趋于稳定. 相似文献
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研究了2397-T87铝锂合金的高周疲劳性能及裂纹萌生扩展行为。结果表明:在应力比R=0.1时,2397-T87铝锂合金L方向、LT方向和ST方向光滑试样(K_t=1.0)的疲劳寿命极限分别约为192,243和151 MPa;缺口试样(K_t=3.0)的疲劳寿命极限分别约为72,78和70 MPa。其疲劳裂纹主要萌生于试样表面,以及氧化物、夹杂等脱落形成的空洞,Al(CuFeMn)第二相杂质粒子。驻留滑移带(PSB)和晶粒取向对其疲劳裂纹早期扩展有重要影响。 相似文献
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通过现场大气暴露实验,利用金相显微镜和SEM等手段分析试样表面和截面形貌,研究了U弯受力状态下包铝与无包铝的LY12和LC4两种铝合金在我国西部盐湖大气环境中的腐蚀行为。结果表明,包铝的两种铝合金的腐蚀主要发生在包铝层,以点蚀为主,未观察到包铝层被穿透现象。无包铝的铝合金试样都发生了明显的沿晶应力腐蚀开裂,其中LY12铝合金在拉应力和压应力下都有较多的应力腐蚀裂纹,LC4铝合金只在拉应力下观察到了裂纹;两种铝合金在压应力下都发生了剥层腐蚀,拉应力下剥层腐蚀受到抑制。 相似文献
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QIAO Lijie LIU Rui XIAO Jimei University of Science Technology Beijing Beijing China 《金属学报(英文版)》1992,5(9):178-182
The effects of stress components on nucleation sites and propagation directions of stress cor-rosion cracks in brass were investigated with specimens under mode Ⅱ and mode Ⅲ loadings.The results indicated that under mode Ⅱ loading,stress corrosion cracks nucleated on the sitewith maximum normal stress component and propagated along the plane perpendieular to themaximum normal stress,under mode Ⅲ loading,the stress corrosion crack was not evident onthe 45°plane due to the general corrosion in aqueous solution with high NH_4OH concentra-tion,while stress corroded in aqueous solution with low NH_4OH concentration, numerouscracks with spacings of 10—150μm were found on the 45°plane with maximum normalstress and no stress corrosion cracks was observed on the plane with maximum shear stress. 相似文献
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Corrosion has a significant impact on the life cycle cost of military aircraft. Fleet experiences show that structural areas around joining elements (rivets, bolts) and faying surfaces are particularly sensitive to corrosion. During the repair currently performed the corrosion usually is blended out, the surface protection applied, the fastener inserted and a new top coat applied. Blending out corrosion often results in a reduction of fatigue life. To restore fatigue life the induction of compressive stress in the area affected is common practice. It is generally accepted that the induction of compressive residual stress extends fatigue life but its impact on the overall corrosion behaviour of alloys is discussed controversially in the literature. For this reason the influence of compressive residual stress on the corrosion behaviour was investigated in a joint experimental project. The compressive residual stress was introduced in different ways on laboratory scale and the specimens artificially weathered to simulate the effect of corrosion. 相似文献
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核反应堆运行时,锆合金包壳的腐蚀和吸氢相伴发生,被锆合金吸收的氢不但会影响锆合金的力学性能,同时对锆合金的耐腐蚀性能也会产生一定的影响,其影响程度与合金成分和腐蚀条件密切相关.氢对Zr-4合金(Zr-1.3Sn-0.2Fe-0.1Cr,质量分数,%)在LiOH水溶液中的耐腐蚀性能影响机理尚不完全清楚.本工作开展了预渗氢... 相似文献
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Satoru Nishikawa Koichi Ooi Makoto Takahashi Takashi Furukawa 《Welding International》2017,31(11):837-845
Shielded metal arc weld metal for type 600 nickel base alloy (alloy 182) is used for weld components in nuclear power plants. To evaluate the intergranular corrosion resistance of alloy 182 after application of shot peening and subsequent thermal ageing treatment at 593–793 K, we conducted the corrosion test (immersed in boiled 16% sulphuric acid +5.7% copper sulphate aqueous solution at 57.6 ks) using specimens of alloy 182. The results show that the intergranular corrosion resistance of alloy 182 subjected to heat treatment at 893 K for 72 ks was improved by shot peening. Also, the intergranular corrosion resistance was not changed by thermal ageing treatment at 593–793 K subsequent to shot peening. Because remaining chromium depletion layers along grain boundaries were still observed by transmission electron microscope (TEM) after shot peening, disappearance of chromium depletion layers cannot be a factor in the improvement of the intergranular corrosion resistance. The results of measurement of surface residual stress by the X-ray diffraction method show that the compressive residual stress introduced by shot peening still remained on the surface of the specimens. Based on these observations, we assumed that chromium depletion layers along grain boundaries near the surface were dissolved by the environment of the corrosion test, the dissolved regions were closed by the compressive residual stress on the surface, and then the remaining chromium depletion layers were protected from the corrosive environment. This assumption explains why the intergranular corrosion resistance was improved although chromium depletion layers remained. 相似文献
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针对老龄飞机7150合金飞机结构普遍存在的剥蚀问题,采用海洋性环境腐蚀试验、透射电子显微镜观测等手段,研究了T6、T73和T77时效态7150合金剥蚀行为。研究结果表明:T77时效态抗剥蚀性能最好,T6时效态抗剥蚀性能最差,T73 时效态介于T77和T6时效态之间。7150-T77合金晶界腐蚀产物的锲力,尚不足以提供其剥蚀扩展所需动力。7150合金时效后的晶界微观组织结构,是抗剥蚀性能的重要决定因素。 相似文献
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The exfoliation corrosion (EFC) susceptibility of several 7000 Aluminium alloys has been studied after a variety of heat treatments using two independent corrosion tests (standard EXCO test and an electrochemical test based on potential transients analysis), together with detailed microstructural examinations. It is proposed that depending on heat treatment EFC may occur via two different mechanisms: inter-granular dissolution induced damage (IDD) or inter-granular fracture induced damage (IFD). The coexistence of these two mechanisms, leading to EFC, and their relative predominance explain the influence of alloy composition and heat treatment on EFC susceptibility via the confrontation of the two corrosion tests. 相似文献