More+
More+

Display Method:      

Display Method:          |     

Cover
Cover
2023, 43(5)   
[Abstract](40) [PDF 3755KB](24)
Abstract:
Review
Progress of cross-scale mechanics in additive manufacturing technology for aeronautical application
YU Zhijie, XU Bihan, WANG Xiangying, SUN Qixing, WANG Yanfei
2023, 43(5): 1 -9   doi: 10.11868/j.issn.1005-5053.2023.000091
[Abstract](99) [FullText HTML](19) [PDF 1809KB](50)
Abstract:
The application of metal additive manufacturing technology and products in the aviation field requires optimized structural design at macroscale and precise manufacture control at microscale. As one of the typical features of additive manufacture, microstructure inevitably affects the material performance. The research has shown that the uniformity, plasticity, and fatigue fracture characteristics of additive manufacturing materials are often inferior to traditional materials, while their strength, hardness, wear resistance, and some microscale properties are often better than traditional materials. The size effect in the micro/nano-scale and the heterogeneous characteristics of materials have a significant impact on metal materials with microstructures. Under different microstructures, materials can achieve a better balance between strength and ductility, which is also applicable to additively manufactured metals. Therefore, the process characteristics of additive manufacturing and the heterogeneities introduced by human design are both expected to significantly improve the comprehensive performance of metals, which have important guiding value for the application of metal additive manufacturing in the aviation field. However, since many of the mechanism of these phenomena are still unclear, the strength-ductility synergistic and antagonistic relationships with other properties of the materials are also worth further research.
Research Paper
Tensile properties of SiC/AZ31 inverse nacre structured composite
HE Bo, LUO Xi, CHANG Chao, ZHAO Ke, LIU Jinling
2023, 43(5): 10 -19   doi: 10.11868/j.issn.1005-5053.2023.000048
[Abstract](49) [FullText HTML](9) [PDF 6590KB](22)
Abstract:
SiC/AZ31 inverse nacre structured composite was prepared by mechanical ball milling and thermal deformation, and the microstructure of the composite was effectively controlled by process control. The microstructure was characterized by X-ray diffraction(XRD)and scanning electron microscopy(SEM), the mechanical properties of the material were tested by quasi-static tensile test, and the strengthening and toughening mechanism and failure mechanism were preliminarily analyzed by combining the microstructure. The results show that the inverse nacre structure obtained by hot deformation process can significantly improve the tensile properties. When the strain hardening ability of the matrix in the inverse nacre structured composite is improved, it can better compensate for the softening effect caused by crack propagation in the hard phase, and the strain hardening ability of the composite is improved. The tensile properties can be controlled by adjusting the size of the lamellar soft phase in the inverse nacre structured composite. When the size of lamellar soft phase is large, the composite has better toughness. When the size of lamellar soft phase is small, the composite has higher strength. The excellent strength and toughness of the inverse nacre structure composite are arising from its structural characteristics, and the continuous hard phase plays a good role in bearing, while the dispersed lamellar soft phase benefits for improving the toughness of the composite. The main strengthening mechanisms of this material include dispersion strengthening, fine grain strengthening, and heterogeneous deformation induced strengthening, and the improvement of toughness are attributed to the crack blunting and deflection induced by lamellar soft phase. In summary, the architecture design of inverse nacre structure is an effective way to obtain high-strength and tough magnesium matrix composite.
Microstructure, mechanical properties and work hardening behavior of SiCp/2024Al composite sheet
XUE Pengpeng, CAO Fuxiang, DENG Kunkun, NIE Kaibo, LIU Li
2023, 43(5): 20 -28   doi: 10.11868/j.issn.1005-5053.2022.000114
[Abstract](38) [FullText HTML](8) [PDF 5811KB](17)
Abstract:
SiCp/2024Al composite material was prepared by ultrasonic assisted semi-solid stirring casting process, and then the two-step hot deformation(extrusion and rolling)was carried out to obtain SiCp/2024Al composite sheet with a thickness of 1 mm, the influence of SiCp content on its microstructure and mechanical properties was investigated. The results show that the rolled 2024 aluminum alloy consists of banded grains and bulk CuAl2 phase. Due to the promotion effect of SiCp on the dynamic recrystallization nucleus of the Al matrix, the grain size of the 2024 aluminum matrix was significantly refined. With the increase of the volume fraction of SiCp, its macroscopic distribution becomes more uniform. The two-step deformation results in the fracture of SiCp and CuAl2 phases, the fracture degree increases with the increase of the volume fraction of SiCp. When the SiCp volume fraction is 15%, the SiCp size is reduced to about 4.9 μm. With the increase of the SiCp volume fraction, the yield strength gradually increases. When SiCp volume fraction is 10%, the comprehensive mechanical properties of SiCp/2024Al composite plate are the best, and its yield strength, ultimate tensile strength and elongation can reach 305, 490 MPa and 8% respectively. With the increase of SiCp volume fraction, the thermal expansion coefficient of SiCp/2024Al composite decreases and the elastic modulus increases, when the SiCp volume fraction is 15%, the elastic modulus can reach 96 GPa, which is 37.1% higher than the 2024 aluminum alloy.
Friction and wear properties of AZ91 alloy reinforced by CNTs coated with MgO
YUAN Qiuhong, ZHOU Guohua, LIAO Lin, WANG Bin, ZHANG Lei, XIAO Shan
2023, 43(5): 29 -38   doi: 10.11868/j.issn.1005-5053.2023.000040
[Abstract](34) [FullText HTML](8) [PDF 6496KB](11)
Abstract:
AZ91 alloy reinforced by carbon nanotubes coated with MgO(AZ91-MgO@CNTs) was prepared by powder metallurgy, hot extrusion and T4 treatment. The influences of MgO@CNTs content and load on the friction and wear property, surface wear morphology and debris topography of AZ91-MgO@CNTs composites were investigated under the dry sliding friction. The results show that MgO@CNTs can improve the wear properties of AZ91-MgO@CNTs. With increasing the content of MgO@CNTs, the strengthening effect of the wear properties of the composite increases and then decreases. Compared with AZ91-CNTs, AZ91-MgO@CNTs has smaller friction coefficient and lower abrasion loss, indicating that the MgO@CNTs is better than CNTs to improve the wear properties of AZ91 alloy. The main wear mechanism of AZ91-MgO@CNTs is abrasive wear under the load of 10 N. When the load is 50 N, there are three wear mechanisms appeared: abrasive wear, oxidation wear and adhesive wear.
Dynamic responses and adiabatic shear behaviors of TC17 and TC4 alloy forgings
CHEN Yuhao, MIN Xiaohua, ZHANG Haiyang, DAI Jincai, ZHOU Yiqun
2023, 43(5): 39 -49   doi: 10.11868/j.issn.1005-5053.2023.000105
[Abstract](31) [FullText HTML](7) [PDF 7902KB](13)
Abstract:
Titanium alloys are widely used in the manufacture of aero-engine blisks due to their low density, high strength, and excellent performance at medium and high temperatures. However, there are few studies on dynamic mechanical properties and adiabatic shear sensitivities of titanium alloy forgings for blisks. In this work, the dynamic mechanical properties of forged TC17 and TC4 alloys at high strain rates were examined by SHPB apparatus, and OM, SEM, EBSD were used to study the adiabatic shear behaviors of the two kinds of alloy. As the strain rate increases, the strength of both alloys increases, thus exhibiting the strain rate strengthening effect. At the same strain rate, TC4 alloy exhibits higher plastic strain and dynamic absorbed energy than those of TC17 alloy. TC17 alloy obtains a basket-weave microstructure after β forging, in which lath α-phases and residual β phases form more phase interfaces. ASBs tend to form at phase interfaces, which lead to a tendency for ASBs to bifurcate during propagating processes. TC4 alloy obtains a bimodal microstructure after α+β forging, and equiaxed primary α-phases show good ductility, which improve the dynamic plastic deformation ability. The regular arrangement of secondary α-phases results in fewer phase interfaces, leading to the difficulty in bifurcation of ASBs during propagating processes. Under dynamic interrupted compression conditions, ASBs in TC17 alloy are occurred earlier, and the localization energy of ASBs is low. Therefore, TC17 alloy has higher adiabatic shear sensitivity, and adiabatic shear sensitivities of both alloys increase with the increase of strain rates.
Solidification structure evolution and crystal growth mechanism of Mg-Sn eutectic alloy
TANG Ling, LIU Wenyi, WANG Yongshan
2023, 43(5): 50 -57   doi: 10.11868/j.issn.1005-5053.2022.000149
[Abstract](25) [FullText HTML](2) [PDF 3938KB](8)
Abstract:
Optical microscope, X-ray diffractometer, scanning electron microscope and energy dispersive spectrometer were used to study the microstructure, phase growth morphology and phase composition of free solidified Mg-Sn eutectic in-situ composites at different solidification stages.The crystal growth mechanism of Mg-Sn eutectic in-situ composite and the effect of cooling rate on the microstructure of the alloy were investigated.The results show that the solidification structure of Mg-Sn hypoeutectic alloy is hexagonal rose-like primary α-Mg phase and eutectic Mg/Mg2Sn lamellar mixed structure. The solidification structure of Mg-Sn hypereutectic alloy is a mixed structure of angular primary Mg2Sn intermetallic compound phase and eutectic Mg/Mg2Sn lamellar structure.With the increase of Sn content, the quantity of primary α-Mg phase decreased and the content of eutectic phase increased. With the increase of cooling rate, the microstructure of the alloy is obviously refined.The α-Mg primary phase is a non-faceted phase, and the primary Mg2Sn intermetallic compound phase is a faceted phase.
Low cycle fatigue properties and fatigue mechanism of DD6 single crystal superalloy under asymmetrical cyclic loading
LI Wei, ZHAO Chunling, ZHANG Xin, WANG Qiang, LI Pu, FANG Xiang, PENG Wenya
2023, 43(5): 58 -66   doi: 10.11868/j.issn.1005-5053.2023.000010
[Abstract](68) [FullText HTML](4) [PDF 4688KB](18)
Abstract:
The low cycle fatigue(LCF) properties of DD6 single crystal superalloy were investigated at 700 ℃ and R of 0.05. SEM was used to study the fracture surface and fracture microstructure. The results show that the LCF life of the alloy decreases with the increase of strain amplitude. LCF properties of the alloy are excellent under asymmetrical cyclic loading. The alloy has no transition fatigue life during LCF tests at all total strain amplitudes. LCF fatigue damage can be dominantly contributed to elastic damage and the plastic deformation is very minimal. The plastic damage increases with the increase of total strain amplitude. The crack initiation site, the fatigue crack propagation area and the final fracture zone can be observed in the fracture surface and all specimens is similar to quasi-cleavage fracture. The fatigue cracks are initiated from the micro-pores on the surface, sub-surface or far from the surface. Far from the surface crack fractures have fish-eye feature. The fatigue crack propagates perpendicularly to main stress at first and then along {111} plane. Typical fatigue striation, cleavage steps and river pattern characteristic are formed on fatigue crack propagation zone. The cleavage plane, slip band and tearing ridge are seen in the final fracture zone. Fracture microstructure analysis shows that the γ′ phase morphology far from the fracture surface still maintains cubic shape, and the slip bands are visible seen near the fracture surface, and secondary cracks are formed along slip bands.
High temperature oxidation microstructure analysis of Ni-based P/M superalloy coated with an inorganic aluminum coating
LI Jialin, YANG Jie, MU Chunhui, JIANG Guojie, LIU Guangxu, WANG Xiaofeng, ZOU Jinwen
2023, 43(5): 67 -75   doi: 10.11868/j.issn.1005-5053.2023.000003
[Abstract](27) [FullText HTML](2) [PDF 3913KB](10)
Abstract:
In this paper, TWL12 + TWL20 inorganic salt aluminum coating was sprayed on the surface of Ni-based P/M superalloy. The microstructure changes of inorganic salt aluminum coating and P/M superalloy after high temperature oxidation at 700, 750 ℃ and 800 ℃ were studied by XRD, SEM, EPMA and TEM. The results show that after high temperature oxidation, the surface structure of the coating peels off, and the aluminum in the coating diffuses with the substrate to form a transition layer composed of oxidation zone, diffusion layer and interdiffusion zone. The oxidation zone is the outermost layer, where is mainly enriched with O and Al elements to form Al2O3 layer. The diffusion layer mainly contains Ni and Al elements, forming NiAl phase and α-Cr phase dispersed in it. Finally, the interdiffusion zone rich in Ti, Cr, Co, Ta and other elements exists between the diffusion zone and the matrix, which is mainly composed of Ni2AlTi phase matrix and σ phase dispersed in it. The analysis shows that the thickness of transition layer changes with the increase of oxidation temperature, it is mainly manifested by the increase of the width of the interdiffusion zone, the increase of the size of α-Cr phase in the diffusion layer and σ phase in the interdiffusion zone, and the growth trend of σ phase along the vertical transition zone is intensified. The oxidation weight gain curve shows that the transition layer exhibits good oxidation resistance during high temperature oxidation at 750 ℃ and 800 ℃ after the surface structure of the coating falls off, it indicates that the TWL12 + TWL20 inorganic salt aluminum coating has the potential to provide high temperature oxidation coating protection for advanced P/M superalloy used in aeroengines.
Mechanical and electromagnetic shielding properties of PIP-2D SiCf/SiC composite materials modified with Al filler
LEI Qiang, DUAN Shichang, DOU Yongqing, LI Qian, LI Houjun, TIAN Jiahao
2023, 43(5): 76 -83   doi: 10.11868/j.issn.1005-5053.2023.000067
[Abstract](20) [FullText HTML](3) [PDF 2169KB](13)
Abstract:
A two-dimensional continuous silicon carbide fiber reinforced silicon carbide composite material(2D SiCf/SiC composite material)was prepared by precursor impregnation cracking method(PIP method)using Al powder as the active filler. XRD, SEM and thermogravimetry were used to analyze the evolution behavior of the microstructure and composition of polycarbosilane pyrolysis products with various Al powder contents. The effects of various Al powder contents on the mechanical and electromagnetic shielding properties of the composites were studied by mechanical testing machine and vector network analyzer. The results show that as the mass fraction of Al filler increases from 0% to 40%, the bending strength of the composite material first increases and then decreases, and the maximum bending strength can reach 383 MPa. The introduction of aluminum filler leads to a gradual increase in the complex dielectric constant of the composite material, and the electromagnetic shielding efficiency gradually increases to 26 dB, which has been greatly improved. This is mainly due to the significant increase in the imaginary part of the complex dielectric constant caused by the increase in the content of Al filler, resulting in a significant improvement in the absorption and shielding efficiency of the composite material.
Construction of acoustic model and simulation of sound absorption of aero-engine composite acoustic liner
YANG Zhiyong, HOU Peng, JIANG Wenge, YANG Lei, ZUO Xiaobiao, GENG Dongbing, ZHU Zhongzheng, LI Hua
2023, 43(5): 84 -96   doi: 10.11868/j.issn.1005-5053.2022.000151
[Abstract](42) [FullText HTML](8) [PDF 2220KB](13)
Abstract:
Acoustic liner is an important component to reduce engine noise. In this work, the modal sound source characteristics of the pipeline under different flow fields were calculated and used as the input boundary for the background flow field calculation and sound propagation calculation of the Actran software, thereby establishing the sound propagation model. The influences of four structural parameters on the sound absorption effect of the muffler plate hole diameter, hole spacing, honeycomb height, and muffler plate thickness in the single-DOF acoustic liner and the double-DOF acoustic liner were studied respectively. The simulation results show that both degrees of freedom acoustic liners exhibit the phenomenon that the smaller the perforation diameter, the better the sound absorption performance within a certain range of hole diameter. The effects of hole spacing, honeycomb height, and muffler thickness on the sound absorption performance are varied with frequency, the double-DOF acoustic liner above 2500 Hz has large dissipation power and good sound absorption effect. Through the contrast verification in the flow tube test, the transmission loss of the acoustic liner of different structures under different excitation sources is compared, and a reasonable and credible simulation method is obtained.
Acoustic emission study on tensile damage and failure behavior of fibre-reinforced aluminum alloy laminates with hole
ZHENG Yingxiao, ZHANG Mai, HU Kejun, DUAN Liuyang, HAN Wenqin, SHI Qinghe, ZHU Fuxian
2023, 43(5): 97 -105   doi: 10.11868/j.issn.1005-5053.2023.000027
[Abstract](39) [FullText HTML](6) [PDF 4298KB](14)
Abstract:
Real-time monitoring of the axial tensile damage process of GLARE laminates with hole was carried out by combining acoustic emission(AE)technology and digital image correlation(DIC)technology. The effect of hole size on the mechanical behavior and failure mechanism was further analyzed. The peak frequency(PF)range of different damage modes was determined based on the k-means method, and the characteristics of AE parameters such as amplitude(PA), energy(E), and cumulative impact number were used to clarify the tensile failure mechanism of GLARE laminates with hole. The results show that there were mainly four damage modes during the entire tensile process of GLARE laminates, namely metal layer damage, matrix cracking, fiber debonding and interface delamination, and fiber fracture. The occurrence of the four damage modes is sequential in time. The size of the hole had a significant impact on the bearing capacity of GLARE, and as the aperture increased, the specimen changed from sudden fracture to ductile fracture at the end of the failure stage.
Ice-ball impact analysis method and verification of three-dimensional braided composites based on surface unit-cell and interior unit-cell modeling
ZHAO Zihao, LIU Lulu, XU Kailong, LUO Gang, ZHAO Zhenhua, CHEN Wei
2023, 43(5): 106 -114   doi: 10.11868/j.issn.1005-5053.2022.000173
[Abstract](30) [FullText HTML](7) [PDF 4010KB](11)
Abstract:
The high-speed ice-ball impact damage research of epoxy resin/carbon fiber 3D four-way braided composites was carried out. Using the air gun impact test system, ice balls with three different impact velocities were used to conduct impact tests. After the test, industrial CT scans were performed on the main damage positions of the test pieces, and the internal damage forms were observed. The composite macro constitutive model based on surface unit-cell and interior unit-cell and a strain rate related material model of the ice were used to establish the finite element model. The simulation model was compared with the test. The results show that the damage of the matrix in the surface unit-cell area is more serious than that in the interior unit-cell area, the damage area of the front surface is generally larger than that of the back surface, the oblique impact angle has an influence on the damage area and damage location. As the impact angle decreases, the damage area of the composite material also decreases. Increasing the thickness of plate can improve the ability to absorb energy and reduce the damage area of the material.
CHALLENGE AND DEVELOPEMENT TRENDS TO FUTURE AERO ENGINE MATERIALS
Fu Hengzhi
1998, 18(4): 52-61  
[Abstract](8060) [PDF 445KB](2593)
Development of advanced polymer composites
CHEN Xiang-bao
2000, 20(1): 46-54  
[Abstract](5787) [PDF 1173KB](2226)
Progress on Electrically Conductive Silicone Rubber
GENG Xin-ling, LIU Jun, REN Yu-zhu, SU Zhengtao, WANG Jing-he
2006, 26(3): 283-288  
[Abstract](5177) [PDF 862KB](1771)
Review and prospect on developments of cast superalloys
CHEN Rong-zhang, WANG Luo-bao, LI Jian-hua
2000, 20(1): 55-61  
[Abstract](5432) [PDF 906KB](1573)
Damage characterization and failure analysis in fiber reinforced composites
XI Niansheng, YU Zhicheng, TAO Chunhu
2000, 20(2): 55-63  
[Abstract](5404) [PDF 348KB](1548)
Resent development in high-entropy alloys and other high-entropy materials
Xiaopeng WANG, Fantao KONG
2019, 39(6): 1-19   doi: 10.11868/j.issn.1005-5053.2019.000170
[Abstract](13118) [FullText HTML](5028) [PDF 1396KB](1492)
Strengthening mechanisms of metal matrix composites
CHEN Jianfeng, WU Gaohui, SUN Dongli, JIANG Longtao
2002, 22(2): 49-53  
[Abstract](5372) [PDF 1023KB](1447)
Study on Fatigue Performance of 7075-T651 Aluminum Alloys
HAN Jian, DAI Qi-xun, ZHAO Yu-tao, LI Gui-rong
2010, 30(4): 92-96  
[Abstract](5629) [PDF 1067KB](1307)
Investigation on Indentation Creep by Depth Sensing Indentation
GAO Yang, WEN Sheng-ping, WANG Xiao-hui, PAN Feng
2006, 26(3): 148-151  
[Abstract](4655) [PDF 495KB](1221)
POLYMERS OBTAINED FROM BENZOCYCLOBUTENES
Huang Farong
1998, 18(2): 53-62  
[Abstract](4955) [PDF 373KB](1218)
Study on In-Plane Anisotropy of 2524 Aluminum Alloy Sheet
GUO Jia-lin, YIN Zhi-min, SHANG Bao-chuan, NIE Bo, HE Zhen-bo
2009, 29(1): 1-6  
[Abstract](4459) [PDF 676KB](1215)
Control and relief of residual stresses in high-strength aluminum alloy parts for aerospace industry
WANG Qiu-cheng, KE Ying-lin
2002, 22(3): 59-62  
[Abstract](4693) [PDF 183KB](1167)
Development and Application of P/M Superalloy
ZOU Jin-wen, WANG Wu-xiang
2006, 26(3): 244-250  
[Abstract](4949) [PDF 1317KB](1145)
Development of honeycomb cell structure and materials
WANG Yu-ying, WU Rong-huang
2000, 20(3): 172-177  
[Abstract](4629) [PDF 662KB](1075)
High-temperature polyimide composites and its application in aeronautical engine
TAN Bi-en, YI Xiao-su
2001, 21(1): 55-62  
[Abstract](4922) [PDF 1606KB](1049)
Progress on Self-Healing Silicon Carbide Ceramic Matrix Composites and Its Applications
ZHANG Li-tong, CHENG Lai-fei, XU Yong-dong, LIU Yong-sheng, ZENG Qing-feng, DONG Ning, LUAN Xin-gang
2006, 26(3): 226-232  
[Abstract](4593) [PDF 2055KB](1034)
Established in 1981
Bimonthly

CN 11-3159/V
ISSN 1005-5053

WeChat

WeChat Public Platform

WeChat ID:hkclxb