Abstract
The hot deformation behavior of the aerospace Ti-10-2-3 alloy was investigated by isothermal compression tests at temperatures of 740 to 820 °C and strain rates of 0.0005 to 10 s−1. The results show that the studied alloy is extremely sensitive to deformation parameters, like the temperature and strain rate. The temperature mainly affects the magnitude of flow stress at larger strains, while the strain rate not only affects the value of flow stress but also the shape of the flow curves. At low strain rates, the flow stress increases with strain, followed by a broad peak and then remains almost constant. At high strain rates, the flow curves exhibit a hardening to a sharp peak at small strains, followed by a rapid dropping to a plateau caused by dynamic softening. In order to describe such flow behavior, a constitutive model considering the effect of deformation parameters was developed as an extension of an existing constitutive model. The modified constitutive model (MC) was obtained based on the original constitutive model (OC) by introducing a new parameter to compensate for the error between the experimental data and predicted values. Compared to the original model, the developed model provides a better description of the flow behavior of Ti-10-2-3 alloy at elevated temperatures over the specified deformation domain.
Highlights
High strength and high toughness titanium alloys have been widely utilized for the fabrication of landing gears’ structure in the aerospace industry due to its high specific strength, excellent fracture toughness, and fatigue resistance [1,2]
Based on Equation (1), the flow behavior of Ti-10-2-3 will be modelled in the prior- and the post-peak stage according to the approach of Lin et al [27] and Hajari et al [28]
The hot flow behavior of Ti-10-2-3 alloy was studied by means of an isothermal compression test over the temperature range of 740 to 820 ◦ C and the strain rate range of 0.0005 to
Summary
High strength and high toughness titanium alloys have been widely utilized for the fabrication of landing gears’ structure in the aerospace industry due to its high specific strength, excellent fracture toughness, and fatigue resistance [1,2]. The effectiveness of numerical simulations is remarkedly affected by the reliability and accuracy of the predictability of the inputted constitutive model [4,5]. In this context, it is of great significance to establish constitutive models with strong applicability and high accuracy. The construction of accurate constitutive model becomes very important [7]
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