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第二届材料科学应用与能源材料国际研讨会

作者： Nan Li Haitao Li Hongtao Liu Changkui Liu AECC Beijing Institute of Aeronautical Materials Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Key Laboratory of Aeronautical Materials Testing and Evaluation Aero Engine Corporation of China Structure Department Shenyang Aircraft Design Research Institute

Anodizing treatment can improve corrosion resistance of aluminum alloy but decrease the fatigue life *** cold expansion before anodizing can increase the fatigue life of the specimen with open-hole structure by 2582% than the anodized *** electron microscopy(SEM) was employed for microstructure and fracture surface *** stress distribution near the sample hole edge was measured to elucidate the strengthening *** results revealed that although anodizing treatment decreases the surface integrity,the cold expansion is an effective method to improve the open-hole structure specimen remarkably.

关键词： SEM Effect of cold expansion on fatigue life of anodized Al alloy

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Analysis of the effect of fretting wear on key structural components of TB6 titanium alloy with actual failure cases

Analysis of the effect of fretting wear on key structural co...

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2018 International Conference on Advanced Electronic materials, Computers and materials Engineering, AEMCME 2018

作者： Kong, Huanping Liu, Changkui AECC Beijing Institute of Aeronautical Materials Beijing China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing China Aviation Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation Beijing China

As the main metal structure materials, titanium alloys have been widely applied in aerospace and other military industries. Titanium alloy develops on the way of high performance and functionalization. Compared with other materials, titanium alloy has high surface integrity and high fretting damage sensitivity. In this paper, the failure case of TB6 high strength titanium alloy key structural parts is taken as the breakthrough point to analyze the effect of surface fretting wear damage on its performance. The appearance inspection, macro and micro morphology observation and energy spectrum analysis were carried out, and the microstructure examination and hardness test were also adopted. The results showed that the fracture property of lug of TB6 high strength titanium alloy was fatigue fracture, and the fretting wear damage of the inner surface of lug hole was the main reason for the fatigue crack initiation. This case is a typical example of titanium alloy structure failure due to fretting wear, which provides reference for the prevention of the recurrence of such faults. © Published under licence by IOP Publishing Ltd.

关键词： Titanium alloys

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Carburized Layer Cracking Analysis of Counterweight Blocks of Speed Controller

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Journal of Physics: Conference Series 2021年第1期2101卷

作者： Tao Jiang Bing Zhang Yimeng Mao Jiale Cheng Xiaodong Shi AECC Beijing Institute of Aeronautical Materials Beijing 100095 China Failure Analysis Center of Aviation Industry Corporation of China Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing 100095 China Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation Aero engine corporation of China Beijing 100095 China New Era Engineering Consulting Co. Ltd. Beijing 100088 China

Trace and fracture analysis, metallographic examination, residual stress testing, and material analysis were carried out, coupled with examining the failure timeline, to analyze the cracking problem of 12CrNi3A steel counterweight blocks under multi-factor coupling. The results show that the cracks of the counterweight blocks are intergranular microcracks in the carburized layer and they are delayed cracks under the joint action of microstructure stress, grinding stress and hydrogen. The delayed cracking of the counterweight blocks is mainly related to abnormal hydrogen absorption during surface treatment and poor grinding quality. The obvious microstructure segregation in raw material and the thicker carburized layer promoted the cracking. The following measures should be comprehensively taken to prevent such failure: strictly controlling raw material quality, hydrogen absorption and stress, as well as increasing the processes to remove hydrogen, reduce stress and stabilize microstructure.

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Service temperature evaluation of cast K465 superalloy turbine vane based on microstructural evolution

Service temperature evaluation of cast K465 superalloy turbi...

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Chinese materials Conference, 2018

作者： Zheng, Zhen Zhou, Jingyi Zhao, Wenxia Zheng, Yunrong AECC Beijing Institute of Aeronautical Materials Beijing100095 China Beijing Key Laboratory on Aeronautical Materials Testing and Evaluation Beijing100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing100095 China Key Laboratory of Aeronautical Materials Testing and Evaluation Aero Engine Corporation of China Beijing100095 China

ISBN: (纸本)9783035713848

The overtemperature in a vane made of cast K465 superalloy was investigated in this paper. The vane was taken from a K465 guide ring after the service for specific period of time. The relationship between the temperature and content of γ´ precipitates was established for the K465 superalloy, which was then used to make the microstructural evolution analysis on failed turbine vane associated with overtemperature. The content of γ´ precipitates in dendritic region and the volume fraction of melting zone in interdendritic region in K465 superalloy were used as the microstructural parameters to check the overtemperature. It is found that there is a sound relationship between the parameters and the temperature. On the basis of this relationship, the microstructural evolution along with temperature variation of the overtemperature K465 turbine vane can be analyzed and the overall service temperature which the K465 guide ring experienced can be evaluated. © 2019 Trans Tech Publications, Switzerland.

关键词： Microstructural evolution

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Failure Analysis of the Aircraft Accessories Graphite Seal Ring

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IOP Conference Series: Earth and Environmental science 2021年第2期781卷

作者： Zhanbin Wang Jinjuan Fan Bing Zhang AECC Beijing Institute of Aeronautical Materials Beijing 100095 China Failure Analysis Center of Aviation Industry Corporation of China Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China

After 1300 hours of operation, the aircraft accessories graphite seal ring parts were overhauled with the aircraft engine. Then the seal assemblies were reinstalled on the engine. The graphite seal ring fractured 1 hour of used. The failure cause of the graphite seal ring was analyzed by appearance inspection, structure relationship analysis of the seal parts, surface and fracture observation, physical performance testing and composition examination. The analysis results show that the physical performance of the failed graphite seal ring met the requirement, and no abnormality was observed in the structural composition. But in the long-term used process, there was mutual wear between the fixing groove of the graphite seal ring and the limiting bracket of the metal static ring seat. As a result, the operating space of graphite seal ring was increased. The overall coordination stability decreases after the secondary assembly. Therefore, when the engine starts, the fluctuating friction occurs between the graphite seal ring and the friction pair, and the lubrication condition was poor, resulting in the graphite ring carrying capacity was too large, and then led to the graphite ring fracture in a short time after maintenance. This leads to fracture of graphite ring in a short time after overhaul. In order to prevent the failure from happening again, this paper gives the corresponding improvement suggestions.

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Fatigue Crack Initiation and Propagation Mechanism of FGH96 PM Superalloy

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IOP Conference Series: materials science and Engineering 2020年第1期729卷

作者： Zhao Kai He Yu-huai AECC Beijing Institute of Aeronautical Materials Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation Aero engine corporation of China Beijing 100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing 100095 China

FGH96 is regarded as a promising powder metallurgy superalloy for high-temperature / pressure turbine disc in aerospace industries due to its high resistance / defect tolerance and high working temperature up to 750 °C. The initiation and propagation mechanism of FGH96 PM superalloy is researched by in-situ fatigue experiments. The result shows that the crack of gap samples initiates and propagates at the same stress level at 25 °C and 300°C. At 300°C, there are no creep characteristics such as the intergranular characteristics found in the sample fracture. The crack at 300°C has a faster initiation and propagation process compared to the crack at 25°C, especially in the late stage of fatigue. The increase of the crack propagation rate of the sample is unrelated to the creep, mainly due to oxidation. Oxidation reduces the fatigue life of materials because it accelerates the initiation and propagation of transgranular cracks.

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Research on Measurement technology of Residual Stress in Rolling Aluminium Alloys

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IOP Conference Series: materials science and Engineering 2020年第2期768卷

作者： Xi Wang AECC Beijing Institute of Aeronautical Materials Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing 100095 China Key Laboratory of Aeronautical Materials Testing and Evaluation Aero Engine Corporation of China Beijing 100095 China

In the measurement of textured materials such as Al Alloy sheet, the traditional method of X-ray residual measurement (sin2ψ method) cannot be applied to these materials. In this paper, 2A97 aluminium lithium alloy was used for the study on residual stress measurement of texted materials. The X-ray diffraction method was used to test the orientation distribution function. The elastic constant of the material was calculated theoretically by Ruess model, Voigt model and Neerfeld-Hill model. And the residual stress was calculated. The blind-hole method was used to verify the results. The blind-hole result agreed well with the Neerfeld-Hill model.

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Effects of gas film hole on mechanical property and oxidative damage of turbine blades

Effects of gas film hole on mechanical property and oxidativ...

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Chinese materials Conference, 2018

作者： Hu, Chunyan Kong, Zhiqiang Liu, Xinling Tao, Chunhu Beijing Institute of Aeronautical Materials Beijing100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing100095 China Aviation key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing100095 China

ISBN: (纸本)9783035713848

With the development of aero-engine with high specific flux, high thrus-weight ratio, and high turbine inlet temperature, it is an effective way to improve the cooling efficiency by designing dense gas film holes on the blade surface of the turbine blades, especially at the intake side. However, the introduction of gas film holes destroys the geometrical integrity of the blade structure, resulting in a multiaxial high stress state of the blade material around the small holes, which seriously affects the strength and life of the cooling blades. In addition, the geometry design of the gas film holes also directly affects the temperature and the oxidation rate of the turbine rotor blades. In this paper, the researches on the mechanical properties and oxidative damage of the gas film holes at home and abroad in recent years have been systematically introduced. The effects of gas film holes on the durability and fatigue properties, the high temperature oxidation behavior of single crystal superalloys, and the thin-walled effect of oxidative damage of gas film holes have been systematically described. © 2019 Trans Tech Publications, Switzerland.

关键词： Turbomachine blades

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Influence of different surface treatments on fatigue life of 7050 Al alloy

Influence of different surface treatments on fatigue life of...

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Chinese materials Conference, 2018

作者： Li, Nan Li, Haitao Zhou, Jingyi Liu, Hongtao Liu, Changkui Qu, Shiyu AECC Beijing Institute of Aeronautical Materials Beijing100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing100095 China Key Laboratory of Aeronautical Materials Testing and Evaluation Aero Engine Corporation of China Beijing100095 China Structure Department Shenyang Aircraft Design Research Institute Shenyang110035 China

ISBN: (纸本)9783035713848

The fatigue life of 7050 Al alloy samples after different surface treatments, i.e., as-machined, anodizing, shot peening, and shot peening followed by anodizing, were tested. The results showed that the shot peening treatment specimens presented the longest average fatigue life. The fatigue life of anodizing treatment specimens decreased by 69.3% and 78.8% at 215 MPa and 260 MPa stress levels than as-machined ones. Introducing the shot peening treatment before anodizing could increase the fatigue life by 220% / 296.9% at 215 MPa/260 Mpa than that only treated by anodizing. The effect of the surface treatments on the fatigue life were studied by performing surface morphology investigation, residual stress measurements and fracture surface analysis. © 2019 Trans Tech Publications, Switzerland.

关键词： Residual stresses

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Feasibility study of NiCoCrFeAl0 .8 Si 0.1 (NbMoTaW) 0.1 denary alloy as a bond coat for thermal barrier coatings: from structural stability to high-temperature oxidation behavior

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Surface and Coatings technology 2025年 512卷

作者： Zhuo Chen Yongzhi Jing Chao Zhang Xiufang Cui Wei Xu Xiang Wang Yongchao Fang Dechang Ma Guo Jin Institute of Surface/Interface Science and Technology Key Laboratory of Superlight Material and Surface Technology of Ministry of Education College of Material Science and Chemical Engineering Harbin Engineering University Harbin 150001 China Northwest Institute for Nonferrous Metal Research Xi an 710016 China No.703 Research Institute China State Shipbuilding Co. Ltd. Harbin 150078 China The Military Industry Program Evaluation Center of Costind of SASTIND Beijing 100048 China Aviation Key Laboratory of Science and Technology on Advanced Corrosion and Protection for Aviation Material Beijing Beijing Institute of Aeronautical Materials Beijing 100095 China

In this study, the feasibility of NiCoCrFeAl 0.8 Si 0.1 (NbMoTaW) 0.1 complex concentrated alloy as a bond coat for thermal barrier coatings (TBCs) was investigated. The alloy bond coat was prepared using plasma spraying technology and compared with the conventional NiCoCrAlY bond coat. The phase composition and microstructural changes of the NiCoCrFeAl 0.8 Si 0.1 (NbMoTaW) 0.1 alloy before and after plasma deposition were analyzed, and the thermal expansion coefficients, microhardness, and oxidation resistance of the two coatings were evaluated. Additionally, a Yttria-Stabilized Zirconia (YSZ) ceramic layer was deposited on the surfaces of both bond coats, forming a complete TBC system, and the evolution of the thermally grown oxide (TGO) layer was studied under different oxidation stages. Results indicate that after plasma spraying, the denary alloy bond coat maintains a single-phase BCC structure with slight compositional segregation, dense microstructure, and effective suppression of segregation of refractory elements due to its high aluminum content. The thermal expansion coefficient of the alloy is comparable to that of NiCoCrAlY, but its microhardness is nearly double that of NiCoCrAlY, with a more uniform hardness distribution. Oxidation testing at 1100 °C revealed that the TGO growth rate of the NiCoCrFeAl-based bond coat TBC is 36 % lower than that of the NiCoCrAlY-based system, demonstrating superior oxidation resistance. This improvement is attributed to the active elements such as Si, Nb, and Mo, which promote the formation of a protective Cr/Al dual-layer oxide film, effectively slowing down further oxidation, internal stress, and the formation of spinel. These findings suggest that the NiCoCrFeAl 0.8 Si 0.1 (NbMoTaW) 0.1 complex concentrated alloy has the potential to serve as a high-performance bond coat in TBC systems, providing superior oxidation resistance, thermal expansion matching, and mechanical integrity at high temperatures.

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