Abstract
The design of lighter and highly loaded aircraft turbo engines is driven by the need of improving their efficiency for a sustainable air propulsion. In this context, forced and self-excited vibrations in bladed disks must be mitigated to avoid HCF damage that jeopardizes the structural integrity of the whole engine. Current vibration prediction methods are not fully reliable due to complexities of the bladed disks design and nature of excitations. To improve the reliability of such methods, it is necessary to (i) investigate key problems like mistuning and nonlinear friction damping and (ii) validate design methodologies. In this chapter, the results of a test campaign to study the effect of mistuning and of underplatform dampers are presented and discussed. The data collected have been used to validate an in-house numerical code. The code exploits an efficient reduction method for large finite-element models of mistuned bladed disks.
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Acknowledgements
This study has been conducted within the ARIAS (“Advanced Research Into Aeromechanical Solutions”) European project, funded by the European Union’s Horizon 2020 research and innovation programme under grant agreement No. 769346.
The authors wish to thank GE Avio s.r.l. for its support and permission to publish this chapter.
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Battiato, G., Firrone, C.M., Pinto, V., D’Ettole, A.G. (2024). An Extensive Test Campaign of a Turbine Bladed Disk in the Presence of Mistuning and Underplatform Dampers, and Numerical Validation. In: Lacarbonara, W. (eds) Advances in Nonlinear Dynamics, Volume I. ICNDA 2023. NODYCON Conference Proceedings Series. Springer, Cham. https://doi.org/10.1007/978-3-031-50631-4_31
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