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1
2022, 37(2): 85-88.
Abstract：
A variety of adhesives are involved in the ship equipment system. Here are introduced the adhesives applied in different parts of the system, discussed the items that need to be assessed, and expounded the assessment methods.
A variety of adhesives are involved in the ship equipment system. Here are introduced the adhesives applied in different parts of the system, discussed the items that need to be assessed, and expounded the assessment methods.
2
2023, 38(1): 85-97.
Abstract：
Titanium matrix composites have been widely used in aerospace, automotive and other fields due to their low density and excellent room and high temperature properties. Here are reviewed the common preparation methods, hot working processes and main properties of discontinuous titanium matrix composites, and are summarized the main problems and solutions in the preparation of titanium matrix composites. Finally, the future development of research and application of titanium matrix composites is pointed out.
Titanium matrix composites have been widely used in aerospace, automotive and other fields due to their low density and excellent room and high temperature properties. Here are reviewed the common preparation methods, hot working processes and main properties of discontinuous titanium matrix composites, and are summarized the main problems and solutions in the preparation of titanium matrix composites. Finally, the future development of research and application of titanium matrix composites is pointed out.
3
Abstract：
Fatigue crack propagation rate of metallic materials is an important index of mechanical property, which is employed for damage tolerance design and fatigue life assessment in engineering application. Paris model is the most popular expression for fatigue crack propagation rate, and the relation of fatigue crack propagation rate and stress intensity factor range at the crack front is believed to meet a power-function rule in the model. The model involves in two material constants of C and m. In this paper, based on some test data published in some literatures, the relationships between material constants of C and m in Paris model for fatigue crack propagation rate of metallic materials of alloy steels, copper alloy, titanium alloy and aluminum alloy were analyzed. The results indicated that the constants of C and m of different types of metallic materials satisfied good linear relationship, namely m=alnC+b, which was not affected by specimen sampling orientation, weld position, and test environment. Stress ratios had great influence on the linear relationship, especially when the stress ratio value was negative. The slopes of the linear models for different metallic materials were not equivalent and the influencing factors should be further researched systematically. The analyzing results would provide reference for fatigue design and application in engineering.
Fatigue crack propagation rate of metallic materials is an important index of mechanical property, which is employed for damage tolerance design and fatigue life assessment in engineering application. Paris model is the most popular expression for fatigue crack propagation rate, and the relation of fatigue crack propagation rate and stress intensity factor range at the crack front is believed to meet a power-function rule in the model. The model involves in two material constants of C and m. In this paper, based on some test data published in some literatures, the relationships between material constants of C and m in Paris model for fatigue crack propagation rate of metallic materials of alloy steels, copper alloy, titanium alloy and aluminum alloy were analyzed. The results indicated that the constants of C and m of different types of metallic materials satisfied good linear relationship, namely m=alnC+b, which was not affected by specimen sampling orientation, weld position, and test environment. Stress ratios had great influence on the linear relationship, especially when the stress ratio value was negative. The slopes of the linear models for different metallic materials were not equivalent and the influencing factors should be further researched systematically. The analyzing results would provide reference for fatigue design and application in engineering.
4
Abstract：
The creep properties and microstructures of Ti-Al-Zr-Mo-Nb-Sn-Si cast titanium alloy at 600~750 ℃ were studied. The results showed that the creep residual elongations were less than 3% at 750 ℃/180 MPa/0.5 h and less than 0.4% at 600 ℃/400 MPa/0.5 h. The time before creep ruptures were more than 2 h and more than 14 h, respectively. The cast titanium aiioy had good creep resistance. There were fine particles in the high temperature creep fracture surface. After creep, the microstructure changed little in the plastic deformation zone, showing widmannstatten structure, and some grain boundaries disappeared and α lamellae became wider. After high temperature creep, dislocations increased obviously and entangled with precipitates.
The creep properties and microstructures of Ti-Al-Zr-Mo-Nb-Sn-Si cast titanium alloy at 600~750 ℃ were studied. The results showed that the creep residual elongations were less than 3% at 750 ℃/180 MPa/0.5 h and less than 0.4% at 600 ℃/400 MPa/0.5 h. The time before creep ruptures were more than 2 h and more than 14 h, respectively. The cast titanium aiioy had good creep resistance. There were fine particles in the high temperature creep fracture surface. After creep, the microstructure changed little in the plastic deformation zone, showing widmannstatten structure, and some grain boundaries disappeared and α lamellae became wider. After high temperature creep, dislocations increased obviously and entangled with precipitates.
5
Abstract：
The hot deformation behavior of the 06Cr23Ni13 stainless steel at different deformation temperatures and strain rates of 0.01 s-1 is studied by Gleeble-3500 instrument, and the effect of deformation temperature on grain boundary content of low coincidence lattice (CSL) is investigated. The results show that the recrystallization degree of the 06Cr23Ni13 stainless steel increases with the increase of deformation temperature. When the deformation temperature is 1 150 ℃, the recrystallization degree of microstructure is the highest, and the austenitic grain is equiaxed. According to the statistics of special grain boundaries of the 06Cr23Ni13 stainless steel under different deformation temperatureby Channel 5 software, the content of the low ∑CSL grain boundaries increases firstly and then decrease with the increase of the dynamic recrystallization degree during the hot deformation process, which reaches its maximum at 1 150 ℃. The low ∑CSL grain boundaries of the 06Cr23Ni13 stainless steel are mainly composed of ∑3, ∑9 and ∑27 grain boundaries.
The hot deformation behavior of the 06Cr23Ni13 stainless steel at different deformation temperatures and strain rates of 0.01 s-1 is studied by Gleeble-3500 instrument, and the effect of deformation temperature on grain boundary content of low coincidence lattice (CSL) is investigated. The results show that the recrystallization degree of the 06Cr23Ni13 stainless steel increases with the increase of deformation temperature. When the deformation temperature is 1 150 ℃, the recrystallization degree of microstructure is the highest, and the austenitic grain is equiaxed. According to the statistics of special grain boundaries of the 06Cr23Ni13 stainless steel under different deformation temperatureby Channel 5 software, the content of the low ∑CSL grain boundaries increases firstly and then decrease with the increase of the dynamic recrystallization degree during the hot deformation process, which reaches its maximum at 1 150 ℃. The low ∑CSL grain boundaries of the 06Cr23Ni13 stainless steel are mainly composed of ∑3, ∑9 and ∑27 grain boundaries.
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