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Titanium aluminum alloy has the advantages of low density, high strength, high-temperature creep resistance and oxidation resistance, and can be used in complex service conditions, especially in high temperature and high pressure and other harsh service environments, but still maintain good mechanical and physical properties, is a kind of material that can be used in the aerospace industry instead of titanium alloys and nickel-based alloys, to achieve the weight reduction of aero-engines, and to increase the thrust-to-weight ratio. Due to the high strength and poor thermal conductivity of titanium aluminum alloys, there are obvious problems such as tool wear, high cutting temperature and poor surface integrity of the work piece during the cutting and machining of the material, which limits the application and promotion of this alloy material. At present, the traditional cutting processing research methods are costly and timeconsuming, compared with the use of finite element method to study the cutting force and temperature is a more economical and effective method. The accurate definition of material in cutting finite element simulation relies on the material's intrinsic model and damage failure model, the current researchers have more studies on the intrinsic model, but in cutting simulation, the intrinsic model alone cannot accurately simulate the process of chip separation, chip separation needs to be defined as the material's damage and damage evolution, but there is a lack of accurate titanium aluminum alloy damage failure model, which affects the accuracy of the cutting simulation. This paper took Ti-48 Al-2 Cr-2 Nb titanium aluminum alloy as the research object, and the failure strain, stress triaxiality and strain rate of this material were obtained through quasi-static tensile test of smooth specimen and notched specimen at different temperatures as well as dynamic tensile test, and the results of the tensile test of smooth specimen found that with the gradual increase of strain, the real stress of the material was also on the trend of increasing, and the material was not observed to have obvious yielding behavior. In addition, as the strain rate increases, the strength of the material also increased, which reflected the effect of strain rate on the strengthening of the material. The ultimate load became larger with the increase of loading speed, and the fracture diameter increased with the increase of loading speed, so the deformation of the material was smaller with the increase of loading speed. In the results of tensile tests of notched specimens, it was found that the failure strain decreases as the stress triaxiality increases. In the case of the same tensile speed and initial diameter, affected by the notched radius, the post-break diameter decreased with the increase of notched radius, indicating that the plastic deformation was gradually enhanced with the increase of notched radius. The dynamic tensile test results showed that with the temperature increased from 20 to 400 ℃, the plastic deformation of the material increased significantly, the stress also increased, indicating that at this time the strain strengthening was greater than the thermal softening, when the temperature continued to rise to 600 ℃, the plastic deformation of the material increased was still obvious, but the stress change was small, indicating that the strain strengthening and temperature softening to reach an equilibrium. The results of dynamic tensile specimen tests at a strain rate of 1000 s-1 showed that as the temperature continued to rise, the post-break cross-sectional area was decreasing, while the failure strain was increasing, indicating that the plastic deformation increased significantly with the rise in temperature. Since the stress triaxiality, strain rate and temperature were multiplicative and uncoupled, the five material parameters of the material could be obtained using the step-bystep fitting method, and the damage failure model was established by fitting the obtained material parameters. On this basis, the cutting process of the material under different cooling conditions of dry cutting, emulsion cooling cutting and liquid nitrogen cooling cutting was simulated, and it was found that serrated chips appeared under all three cooling conditions when the cutting speed of vc=150 m·min-1, and the degree of serrated chip morphology under the emulsion cooling conditions was smaller than that of dry cutting and liquid nitrogen cooling cutting, and different degrees of unitary chips appeared in both dry cutting and liquid nitrogen cooling cutting. The dry cutting and liquid nitrogen cooling cutting both showed different degrees of unit chips and even fracture, while the emulsion chips were still in continuous chip state and no unit chips appeared. Comparing with the chip morphology and cutting force during the actual right-angle cutting test, it was found that the chip morphology in the simulation and the actual test was basically consistent, indicating that the cutting simulation damage model of titanium-aluminum alloy established in this paper had high accuracy. The relative error between the simulation results of cutting force and the test results was within 10%, and the change trend of the simulation value was consistent with the change trend of the measured value, which also verified the accuracy of the damage failure model. The establishment of the damage failure model provided more accurate guidance for the cutting simulation of titanium aluminum alloy.
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Basic Information:
DOI：10.13373/j.cnki.cjrm.XY24090015
China Classification Code:TG506
Citation Information:
[1]Feng Shuo,Wang Jinhui,Li Na ,et al.Damage Failure Model of Titanium Aluminum Alloy for Cutting Simulation[J].Chinese Journal of Rare Metals,2026,50(02):211-219.DOI:10.13373/j.cnki.cjrm.XY24090015.
Fund Information:
国家自然科学基金项目(52005215); 山东省自然科学基金项目(ZR2023ME077); 山东省高等学校“青创团队计划”项目(2023KJ110)资助
2026-02-15
2026-02-15