Abstract
Near- titanium alloys have extensive applications in high temperature structural components of aircrafts. To manufacture complex-shaped titanium alloy panel parts with desired microstructure and good properties, an innovative low-cost hot stamping process for titanium alloy was studied in this paper. Firstly, a series of hot tensile tests and Scanning Electron Microscope (SEM) observations were performed to investigate hot deformation characteristics and identify typical microstructural evolutions. The optimal forming temperature range is determined to be from 750 °C to 900 °C for hot stamping of TA15. In addition, a unified mechanisms-based material model for TA15 titanium alloy based on the softening mechanisms of recrystallization and damage was established, which enables to precisely predict stress-strain behaviors and potentially to be implemented into Finite Element (FE) simulations for designing the reasonable processing window of structural parts for the aerospace industry.
Highlights
Titanium alloys, as advanced lightweight materials, have been extensively used in the aerospace industry, due to their high strength, low density, and good corrosion resistance [1]
The non-isothermal feature of hot stamping process results in the deformation temperature varies with different locations and proceeding of deformation, which determines the formability and post-form microstructure
The developed material model can be further implemented into Finite Element (FE) simulations to determine optimal process window and provide useful guides for manufacturing structural panel parts for the aerospace industry
Summary
As advanced lightweight materials, have been extensively used in the aerospace industry, due to their high strength, low density, and good corrosion resistance [1]. In terms of relatively simple-shaped components, isothermal hot stamping using rigid dies is widely used enabling forming titanium alloy sheets under the optimal process conditions. To address the above limitations, a novel hot stamping process is proposed and investigated in this study In this process, a titanium alloy sheet is initially heated and soaked at the target temperature in a furnace. The non-isothermal feature of hot stamping process results in the deformation temperature varies with different locations and proceeding of deformation, which determines the formability and post-form microstructure. Using the obtained stress-strain relationships, the performed research established a mechanisms-based constitutive material model for near-α titanium alloy under hot stamping condition with considerations of a series of microstructural evolutions, especially recrystallization and damage for the softening. The developed material model can be further implemented into FE simulations to determine optimal process window and provide useful guides for manufacturing structural panel parts for the aerospace industry
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