A reduced-order model for stall flutter of turbomachinery is presented. The model is based on simplified physics (actuator disk modeling of bladerows, typical section aeroelastic model) and the measured steady performance characteristic. The model is not intended to be predictive, though it has been shown to be “tunable” to stability measurements of the test rig. The objective of the effort is to estimate the relative sensitivity of flutter damping to system parameters. It is found that predictions are in good agreement with measured test rig data and industry experience.
- Applied Mechanics Division
Reduced-Order Modeling and Experiment for Turbomachinery Stall Flutter
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Copeland, GS, & Rey, GJ. "Reduced-Order Modeling and Experiment for Turbomachinery Stall Flutter." Proceedings of the ASME 2002 International Mechanical Engineering Congress and Exposition. 5th International Symposium on Fluid Structure Interaction, Aeroelasticity, and Flow Induced Vibration and Noise. New Orleans, Louisiana, USA. November 17–22, 2002. pp. 139-145. ASME. https://doi.org/10.1115/IMECE2002-33056
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