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| Asıl Yazarlar: | , , |
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| Materyal Türü: | Recurso digital |
| Dil: | |
| Baskı/Yayın Bilgisi: |
Zenodo
2026
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| Konular: | |
| Online Erişim: | https://doi.org/10.5281/zenodo.20004511 |
| Etiketler: |
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İçindekiler:
- <p>The energy method is widely used for flutter stability<br>analysis of turbomachinery due to its simplicity and low<br>computational cost, relying on the evaluation of aerodynamic<br>work and structural dissipation over a vibration cycle. However,<br>in some cases, when applied to systems with nonlinear contact<br>forces, such as those at blade roots, interlocked shrouds, or<br>underplatform dampers, the method can underestimate frictional<br>energy dissipation, leading to inaccurate predictions of limit<br>cycle oscillation amplitudes. This work investigates the use of<br>the energy method to predict the flutter-saturated response of<br>low-pressure turbine rotors with nonlinear friction interfaces.<br>To assess these limitations, two structural representations<br>are considered: a reduced-order mass–spring model and a<br>detailed finite element model of a realistic LPT rotor. In both<br>cases, the results are compared with reference solutions obtained<br>from direct time-integration simulations. For configurations<br>where the standard formulation fails, a corrected approach that<br>accounts for nonlinear structural effects in the contact regions<br>is proposed. This correction significantly improves agreement<br>with reference solutions for the detailed realistic model while<br>preserving the computational efficiency. The equations of the<br>standard and the corrected energy methods are consistently<br>derived using asymptotic techniques from both bladed-disk<br>models.</p>