The effect of frequency and sample shape on fatigue behaviors of DZ125 superalloy

The effect of frequency and sample shape on fatigue behaviors of DZ125 superalloy are systematically studied. The results show that fatigue fracture still occurs above the cycle of 10⁸ for tests carried out at the frequency of f = 20 kHz and stress ratio R = ?1, so the traditional fatigue limit at cycle of 10⁷ is not appropriate for fatigue design. Fatigue fracture surfaces are perpendicular to stress axis for cylindrical and plate specimens, and the fatigue cracks originate from the extra surface of the specimens. Fatigue crack is apt to propagate from cutting direction to forward direction, which occurs mainly in the second propagation stage at higher stress amplitude. There is an obvious frequency effect for DZ125 superalloy. The higher the test frequency is, the more serious the effect of frequency on fatigue behaviors of the alloy. After the frequency correction, the ultra-high cycle fatigue S-N curve well coincide with the traditional fatigue S-N curve.     

镍基单晶超合金Ni/Ni3Al晶界的分子动力学模拟

在镍基单晶超合金中，由于单晶Ni的晶格常数比单晶Ni₃Al的稍小，在Ni/Ni3Al晶界面 上必然要出现错配.采用分子动力学模拟了镍基单晶超合金的Ni/Ni₃Al晶界的结 构，考虑 了两个不同的初始模型，并进行了分子动力学弛豫.弛豫的结果均表明：由于晶格的差异形 成的错配能不是通过长程晶格错配的方式来释放，而是通过在局部区域形成位错的方式释放 的.由于Ni₃Al相周围Ni相环境的不同，形成的位错也有所不同. 关键词： 镍基单晶超合金 晶界 分子动力学模拟     

Synchrotron Microbeam Diffraction Study of the Microstructure and the Chemical Composition in a Monocrystalline Ni-Base Turbine Blade After a Thermomechanical Mission Test

High-performance turbine blades composed of monocrystalline Ni-base / superalloys are often protected by coatings to resist the high-temperature corrosive atmosphere environment applications. During applications severe thermal and mechanical loads cause drastic and complicated changes in the microstructure and the chemical composition, also combined with strong lateral gradients of both temperature and stress. Microbeam X-ray diffraction experiments with a spatial resolution of about 5 m enabled the determination of both the microstructural and the chemical composition gradients within material volumes of the sizes of the order of about 1 mm³ or smaller. The high angular and spatial resolution was achieved by a special focusing technique using a Bragg–Fresnel focusing monochromator at the BM5 beamline of the ESRF synchrotron at Grenoble. The X-ray diffraction experiments were complemented and supported by electron microscopy investigations of the microstructure and the chemical composition.     

火焰原子吸收光谱法测定镍基高温合金中的镉

采用火焰原子吸收光谱法测定镍基高温合金中的镉,样品以硝酸-氢氟酸-水混合溶液(1+1+1)前处理,选择Cd 228.8 nm为分析线进行测定,并通过标准加入法校正基体效应。考察了消解酸的选择,仪器工作参数的调整,基体和共存离子对镉测定的影响。结果表明,镍基高温合金中镉的检出限为0.088μg/g。加标回收率为94.1%~109%,结果的相对标准偏差(RSD,n=8)在0.54%~1.6%。方法操作简便、分析速度快、准确度好,适用于镉含量在0.0001%~0.001%的镍基高温合金中的测定。     

微波消解–电感耦合等离子体发射光谱法测定DD6单晶合金中铝、铬、钴

建立电感耦合等离子体发射光谱法测定DD6单晶高温合金中铝、铬、钴元素含量的方法。采用密闭微波消解法对样品进行前处理,利用模拟溶液分别考察基体元素和共存元素的光谱干扰及非光谱干扰对测定结果的影响,确定了铝、铬、钴的分析谱线分别为394.401,267.716,228.616 nm,通过基体匹配法对非光谱干扰进行补偿。待测元素在各自的质量浓度范围内与光谱强度呈良好的线性关系,相关系数均为0.9999,铝、铬、钴的检出限分别为0.110,0.018,0.003 μg/mL。测定结果的相对标准偏差为0.99%~1.21%(n=11),铝、铬、钴的加标回收率在分别为96.45%~103.69%,98.20%~99.40%,100.22%~102.85%。该方法简便、快速,具有较高的准确度,适用于镍基单晶高温合金中铝、铬、钴元素的测定。     

激光剥蚀-电感耦合等离子体质谱对高温合金中17种痕量元素的测定

建立了镍基高温合金中Sc、Cu、Zn、Ga、Ge、As、Ag、Cd、In、Sn、Sb、Te、Ce、Hf、Tl、Pb、Bi17种痕量元素的激光剥蚀-电感耦合等离子体质谱测定方法。对激光剥蚀进样及质谱分析条件进行了优化,通过激光对样品表面的层层剥蚀顺利完成了对低沸点杂质元素的测定。采用格栅扫描采样,严格控制样品的聚焦位置和散焦距离以保证采样的准确性,由高温合金系列标准物质建立了18种痕量元素的校正曲线,其中14种痕量元素的线性相关性较好(r2≥0.99),In、Sn、Sb、Ce、Tl、Pb、Bi等超痕量元素的检出限和气体空白分别低于或接近0.000 005%和0.000 001%。方法对镍基高温合金样品中Cu、Ga、Ag、Cd、In、Sn、Sb、Te、Hf、Tl、Pb和Bi等痕量元素的测定结果与参考值吻合较好,且大部分元素的RSD(n=4)小于或接近30%。     

过硫酸铵氧化-亚铁容量法测定高温合金及钢铁中高铬含量

在航空行业标准HB 5220.15-1995的基础上,采用过硫酸铵氧化-亚铁容量法测定高温合金及钢铁中高铬含量的试验方法,通过试验确定了试样量、硫酸和磷酸等试剂用量。该方法对高温合金样品中铬含量测定结果的相对标准偏差不大于0.13%(n=8),回收率为100.04%~100.49%。方法稳定性和重复性好,适用于铬含量为30.00%~50.00%的高温合金及钢铁样品。     

Gamma ray shielding capabilities of rhenium-based superalloys

ABSTRACT

Because of the high radiation dose in applications involving nuclear reactors, medical treatments etc., it is important to reduce the exposure to radiation of areas and workers. In this study, we were examined gamma ray shielding parameters of the newly produced Re-based superalloys. Mass attenuation coefficient (µ/ρ) of the alloys were obtained experimentally at 81, 276, 302, 356, 383 keV photon energies emitted from ¹³³Ba radioactive source using Ultra Ge detector. The experimental results were compared with the values obtained by the WinXCOM program and were found to be in perfect agreement with each other. Additionally, effective atomic number (Z_eff) and electron density (N_eff) were determined for produced Rhenium (Re) based super alloys in the energy range 1 keV–100?GeV. S5 sample which has maximum Rhenium percentage own the largest µ/ρ and Z_eff values. Moreover, by using Geometric Progression (GP) approximation, EABF and EBF were computed for the superalloys depending on the energy and penetration depths. It has been deduced that the values of EABF and EBF are minimum in the medium energy region. EBF and EABF values of the alloys have changed depending on the equivalent atomic number. Among alloy samples under study, S5 superalloy is the best for gamma ray shielding. However, in general, considering the radiation energies used in many applications, all the alloys under study have satisfactory radiation absorption properties.     

Very-High-Cycle-Fatigue of in-service air-engine blades, compressor and turbine

In-service Very-High-Cycle-Fatigue(VHCF)regime of compressor vane and turbine rotor blades of the Al-based alloy VD-17and superalloy GS6K,respectively,was considered.Surface crack origination occurred at the lifetime more than 1500 hours for vanes and after 550 hours for turbine blades.Performed fractographic investigations have shown that subsurface crack origination in vanes took place inspite of corrosion pittings on the blade surface.This material behavior reflected lifetime limit that was reached by the criterion VHCF.In superalloy GS6K subsurface fatigue cracking took place with the appearance of flat facet.This phenomenon was discussed and compared with specimens cracking of the same superalloy but prepared by the powder technology.In turbine blades VHCF regime appeared because of resonance of blades under the influenced gas stream.Both cases of compressor-vanes and turbine blades in-service cracking were discussed with crack growth period and stress equivalent estimations.Recommendations to continue aircrafts airworthiness were made for in-service blades.     

高温合金活性剂激光微焊接接头的组织性能研究

采用配方均匀设计法,配制了SiO2-MnO2-CaO-TiO2-CaF2-NaF多组元活性剂,利用微型脉冲激光器对500 m厚GH4169高温合金进行了活性剂激光焊接试验。分析并讨论了焊接接头的显微组织和力学性能。试验结果表明,与传统激光焊相比,所配制的20种活性剂均增加了焊缝熔深,并且其中F12系混合活性剂增加熔深能力最为显著,使焊缝深宽比增加了159%,证明通过使用活性剂来增加微激光焊焊缝熔深,降低高温合金板激光焊接的成本是可行的。在活性剂作用下,焊缝显微组织仍由柱状晶和等轴晶组成,接头抗拉强度达到927 MPa,为母材强度的92.7%。