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Zhang S.,Aerospace Research Institute of Materials And Processing Technology | Zhang S.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Zhang S.,National Key Laboratory of Science and Technology on Advanced High Temperature Structural Materials
Hangkong Cailiao Xuebao/Journal of Aeronautical Materials | Year: 2016

The total strain-controlled low cycle fatigue (LCF) behaviors of directionally solidified (DS) superalloy DZ408 at 950℃, 1000℃ and 1050℃ for R=0.05 were investigated. The results of LCF tests indicate that the mean stress relaxation is occurred under asymmetric straining. The rate of mean stress relaxation is increased with the increase of temperature and strain amplitude. The alloy has Massing characteristic at 950℃, 1000℃ and 1050℃ for R=0.05. All the LCF data obtained under various temperatures are well correlated by the modified SWT approach for lifetime prediction, and also the relationship between temperature and parameter of modified SWT model are obtained. © 2016, Chinese Journal of Aeronautics. All right reserved. Source


Liu L.Y.,Aerospace Research Institute of Materials And Processing Technology | Fan Y.W.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Wan Q.,AVIC Testing Innovation Cooperation
Materials Science Forum | Year: 2015

Solidification behaviors of IC10 alloy with different titanium content were investigated by isothermal solidification method. Volume percentage of liquid and precipitation temperature of primary MC type carbide, eutectic and secondary γ′ phase were investigated. The results showed that with the increase of Ti content in the alloy, the liquidus, solidus and MC carbide formation temperatures decreased, on the contrary, the formation of γ+γ′ eutectic and secondary γ′ increased. For the IC10 alloy with 1.5% titanium content, it is earlier for the interdendritic pools to be divided into the parts. At this condition, melted portion of the alloy resided during isothermal process. As a result, the castability of the IC10 with 1.5% titanium is thus the lowest. © (2015) Trans Tech Publications, Switzerland. Source


Gao S.,Aerospace Research Institute of Materials And Processing Technology | Gao S.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Pang X.-H.,Aerospace Research Institute of Materials And Processing Technology | Liang H.-L.,Aerospace Research Institute of Materials And Processing Technology
Yejin Fenxi/Metallurgical Analysis | Year: 2015

With water-hydrochloric acid-hydrofluoric acid-nitric acid mixed acid system dissolving sample, a method for determination of magnesium, vanadium, chromium, iron, cobalt, copper, manganese, molybdenum and tungsten in TG6 titanium alloy was established by inductively coupled plasma atomic emission spectrometry(ICP-AES) at the atomization flow rate of 0.65 L/min. The effect of titanium matrix and coexisting elements was investigated, and the analytical lines of each testing elements were Mg 285.2 nm, V 310.2 nm, Cr 283.5 nm, Fe 259.9 nm, Co 238.8 nm, Cu 213.5 nm, Mn 257.6 nm, Mo 202.031 nm, W 207.9 nm. Matrix effect was eliminated by matrix matching. The detection limit was 0.003-0.005 7 μg/mL. The relative standard deviations (RSDs) for determination of actual samples by the proposed method were 0.26%-13.6%, and the standard addition recoveries were 93%-110%. Simulated TG6 titanium alloy sample was prepared according to the nominal composition Ti-5.8Al-4Sn-4Zr-0.5Ta-0.7Nb-0.4Si-0.06C of TG6 titanium alloy, whose determination results by the experimental method were basically consistent with the theoretical value. ©, 2015, Central Iron and Steel Research Institute. All right reserved. Source


Tao C.,Aerospace Research Institute of Materials And Processing Technology | Tao C.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Liu C.,Aerospace Research Institute of Materials And Processing Technology | Liu C.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation
Materials China | Year: 2014

Pitting, filiform corrosion, intergranular corrosion, stress corrosion and hydrogen embrittlement are the common corrosion failure modes in the carrier-based aircraft. The formation mechanisms, failure phenomena, failure characteristics and influencing factors of these five failure modes are introduced in this paper. Several typical cases of corrosion failure which are induced by design, manufacturing processes, materials and other factors are presented respectively. The prevention and improvement measures are given, according to the failure reason in each case. Some recommendations for the design, manufacturing processes and materials selection are also discussed here. The results shows that the corrosion control of the aircrafts is a systematic project. In the design, it is necessary to take full account of controlling the factors which affect the corrosion, and pay attention to the details of the anti-corrosion design; In the selection of reasonable anti-corrosion processes, the material and process should get a mutual appropriate match, furthermore, the material and its process should adapt to the environment demands. ©, 2014, Materials China. All right reserved. Source


Liu X.L.,Aerospace Research Institute of Materials And Processing Technology | Liu X.L.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Zhao K.,Aerospace Research Institute of Materials And Processing Technology | Zhao K.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation
Applied Mechanics and Materials | Year: 2014

Powder metallurgy (P/M) superalloy has not only been the primary material of turbine disk but also the main material of packing disk, packing ring and baffle plate of the aero-engine. Among these components, some parts are very thin, for example, the thinnest of baffle plate is only 2mm. The thin plate component was subjected to complex load, and the failure mode was synthetical. Some parts of component are subjected to impact load or impact-fatigue load although the nominal load of this component is fatigue load, more than one baffle plates have cracked through fast expansion and burst multiple debris because of the different local load type for the same component. It is very useful to investigate the effect on tensile and impact properties by specimen shape and shot peening. In this article, the different tests were carried out, including different specimen shape, temperature and surfaces. The results indicated that fracture strength ób and elongation δ5 were not affected by shape of specimen of P/M superalloy. Rod or plate specimens may be used to characterize the static properties of material. Shot peening would decrease the elongation, δ5 (at room temperature and 650°C) and impact work, but it did not reduce the fracture strength σb. In order to utilize adequately the component subjected to complicated loads, the surface state of the component may be treated distinctively according to the specific local load. © (2014) Trans Tech Publications, Switzerland. Source

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