Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation

Beijing, China

Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation

Beijing, China
SEARCH FILTERS
Time filter
Source Type

Liu X.-L.,Aerospace Research Institute of Materials And Processing Technology | Liu X.-L.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Xu Y.-M.,Beihang University | Tao C.-H.,Aerospace Research Institute of Materials And Processing Technology | Tao C.-H.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation
Rare Metals | Year: 2014

Vibration fatigue is the main failure mode of compressor blade. Evaluating the vibration stress of blade that leads to cracking is very useful for analysis of vibration fatigue. In this paper, fatigue stress estimation methods by quantitative fractography were studied through experimental blade and in-service first-stage compressor blade in order to evaluate the initiation vibration stress of in-service blade. The analysis process of initiation vibration stress was established. The evaluating result of vibration stress of in-service blade subjected to centrifugal force and bending vibration stress agrees with aero engine test result. It is shown that the evaluation method can not only evaluate the equivalent fatigue stresses of different crack depths but also yield the initiation equivalent fatigue stress. © 2014 The Nonferrous Metals Society of China and Springer-Verlag Berlin Heidelberg.


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.


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.


Hu C.,Aerospace Research Institute of Materials And Processing Technology | Hu C.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Jiang T.,Aerospace Research Institute of Materials And Processing Technology | Jiang T.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | And 2 more authors.
Jinshu Rechuli/Heat Treatment of Metals | Year: 2014

Two fastening screws of fluid pressure cylinder head were fractured during test running. The feature and failure cause of the screws were analyzed by fracture observation, metallographic examination and hardness test. The results show that the fracture mode of the screw A was overload breakage which was relevant to the overloading assembly stress and led to torsion shear cracking; The screw B was fatigue failure because of the decarburized layer and the additional tensile stress in the assembly process which accelerated fatigue failure. It is proposed that the heat treatment process and the assembly stress should be controlled strictly.


Xiao W.,Aerospace Research Institute of Materials And Processing Technology | Xiao W.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Tao C.H.,Aerospace Research Institute of Materials And Processing Technology | Tao C.H.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | And 6 more authors.
Advanced Materials Research | Year: 2013

Acoustic principle of ultrasonic measurement for stress field was introduced briefly. Longitudinal critically refracted (Lcr) wave was applied to study a non-uniform stress field in high strength 7050-T7451 aluminum alloy. Error sources of testing were investigated as well. The results indicate that ultrasound can be conveniently used to characterize non-uniform stress field with sufficient accuracy but without destruction. The measuring results represent mean stress existing in propagation path of ultrasonic. Stress field mapped by ultrasound has good coincidence with actual stress field. Temperature and coupling are main error sources of testing. As long as temperature maintains invariable, it is easy to characterize stresses with error less than 40 MPa even in different coupling condition and with other artifical variable. The measurement error induced by coupling was tolerable and reduced with increasing stress. This technique will provide a non-destructive method to measure residual stress in structures. © (2013) Trans Tech Publications, Switzerland.


Zhao K.,Aerospace Research Institute of Materials And Processing Technology | Zhao K.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | He Y.H.,Aerospace Research Institute of Materials And Processing Technology | He Y.H.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | And 2 more authors.
Advanced Materials Research | Year: 2014

Multiaxial fatigue life of 50CrVA spring steel standard specimens and eccentric specimens under proportional loading was studied with MTS 809 tension-torsion electro-hydraulic servo tester. Both kinds of specimens were calculated by the finite element software ABAQUS and the fatigue life of specimens were predicted based on the finite element results. The results show that the additional bending moment will obviously reduce the life of specimens; only the Manson-Halford model and modified Manson-Halford model can obtain satisfactory results in many prediction models selected. © (2014) Trans Tech Publications, Switzerland.


Kong H.,Aerospace Research Institute of Materials And Processing Technology | Kong H.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Liu D.,Aerospace Research Institute of Materials And Processing Technology | Liu D.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | And 2 more authors.
Procedia Engineering | Year: 2015

Left 1# u-shaped boltfractured when the automobile running 3766 km in testing process, then 2# u-shaped bolt was repacked. Left 2# u-shaped bolt and right 3# u-shaped bolt were fractured whenthe automobile running 7778 km. The failure mode and cause were analyzed by macro and micro observation, metallographic examination, hardness and tensile property testing, dimension examination.The results showed that u-shaped bolts were fatigue fracture. U-shaped bolts' failure was related with densely distributed surface micro cracks, surface decarburization appearance, small dimension, and low strength of material. © 2015 Published by Elsevier Ltd.


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.


Zhang B.,Aerospace Research Institute of Materials And Processing Technology | Zhang B.,Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation | Cao X.-G.,Nantong Higher Normal Institute | Liu D.-L.,Aerospace Research Institute of Materials And Processing Technology | And 3 more authors.
Transactions of Nonferrous Metals Society of China (English Edition) | Year: 2013

As-cast single crystal (SC) superalloy samples were shot peened and then annealed at different temperatures to investigate the effect of annealing temperature on the surface recrystallization behavior of the SC superalloy. The results show that the depth of recrystallized layers increases with the increase of annealing temperature. Below 1200 C, the recrystallization depth climbs slowly with temperature rising. Above 1200 C, the recrystallization depth increases sharply with the rise of temperature. The morphology of recrystallized grains is significantly affected by annealing temperature. Below the γ′ solvus, cellular recrystallization may be observed. Above the γ′ solvus, recrystallization occurs through the growth of well developed recrystallized grains. In addition, the microstructure evolution of recrystallized grains at the homogenization annealing temperature was studied. It is found that recrystallized grains first nucleate in the dendritic core areas on the shot-peened surface and then grow inwards along the dendritic core areas. With the dissolution of the coarse γ′ precipitates and γ′/γ′ eutectics in the interdendritic areas, the recrystallized grain boundaries move through the interdendritic areas. Finally, the fully developed grains nearly have a uniform depth. The dissolution of primary γ′ precipitates is a critical factor influencing the recrystallization behavior of SC superalloys. © 2013 The Nonferrous Metals Society of China.


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.

Loading Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation collaborators
Loading Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation collaborators