Sensitivity Analysis of the Johnson-Cook Model for Ti-6Al-4V in Aeroengine Applications
Titanium alloys, such as Ti-6Al-4V, are crucial for aeroengine structural integrity, especially during high-energy events like turbine blade-out scenarios. However, accurately predicting their behavior under such conditions requires the precise calibration of constitutive models. This study presents...
Saved in:
| Main Authors: | , , , , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2024-12-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/12/1/3 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | Titanium alloys, such as Ti-6Al-4V, are crucial for aeroengine structural integrity, especially during high-energy events like turbine blade-out scenarios. However, accurately predicting their behavior under such conditions requires the precise calibration of constitutive models. This study presents a comprehensive sensitivity analysis of the Johnson-Cook plasticity and progressive damage model parameters for Ti-6Al-4V in blade containment simulations. Using finite element models, key plasticity parameters (yield strength (<i>A</i>), strain-hardening constant (<i>B</i>), strain-rate sensitivity (<i>C</i>), thermal softening coefficient (<i>m</i>), and strain-hardening exponent (<i>n</i>)) and damage-related parameters (<i>d</i>1, <i>d</i>2, <i>d</i>3, <i>d</i>4, and <i>d</i>5) were systematically varied by ±5% to assess their influence on stress distribution, plastic deformation, and damage indices. The results indicate that the thermal softening coefficient (<i>m</i>) and the strain rate hardening coefficient (<i>C</i>) exhibit the most significant influence on the predicted casing damage, highlighting the importance of accurately characterizing these parameters. Variations in yield strength (<i>A</i>) and strain hardening exponent (<i>n</i>) also notably affect stress distribution and plastic deformation. While the damage evolution parameters (<i>d</i>1–<i>d</i>5) influence the overall damage progression, their individual sensitivities vary, with <i>d</i>1 and <i>d</i>4 showing more pronounced effects compared to others. These findings provide crucial guidance for calibrating the Johnson-Cook model to enhance aeroengine structural integrity assessments. |
|---|---|
| ISSN: | 2226-4310 |