Piezoelectric-based vibration reduction of turbomachinery bladed disks via resonance frequency detuning

Jeffrey L. Kauffman, George A. Lesieutre

Research output: Contribution to journalArticlepeer-review

42 Scopus citations


Piezoelectric-based resonance frequency detuning can alleviate unwanted vibration of turbomachinery blades, thus reducing the dangers of high-cycle fatigue while also decreasing the blade weight. This semiactive approach applies to structures that are subjected to frequency-sweep excitation and involves altering the structural stiffness (here, by switching the piezoelectric electrical boundary conditions) to avoid a resonant condition, thus limiting the blade response. Detuning requires two switches per resonance/excitation frequency crossing, including a switch back to the original the original state, many fewer than other semiactive approaches that require four switches per cycle of vibration. Resonance frequency detuning applies to any mode of vibration with a positive electromechanical coupling coefficient, and it provides the greatest normalized vibration reduction for slow sweeps, low damping, and high coupling coefficient. Yet even for a moderate sweep rate α = 10 -4 and modal damping θ = 0.1%, optimally detuning a structure with an electromechanical coupling coefficient k 2 = 10% provides the same vibration reduction as increasing either the sweep rate or modal damping by an order of magnitude. With a lower sweep rate α = 10 -5 and modal damping θ = 0.01%, detuning with a coupling coefficient of only k 2 = 3% provides equivalent vibration reduction as an order of magnitude increase in sweep rate or modal damping.

Original languageEnglish (US)
Pages (from-to)1137-1144
Number of pages8
JournalAIAA journal
Issue number5
StatePublished - May 2012

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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