A modal stability (MS) method is presented for the quick and accurate prediction of the stability of aerodynamically excited turbomachinery using real eigenvalue/eigenvector data obtained from a rotordynamics model. The modal stability method provides a means to compare the work of stabilizing damping forces to the work of destabilizing aerodynamic cross-coupled stiffness forces to predict the onset of whirl instability. The MS method thus indicates that unstable or self-excited whirling (sometimes called whipping) at one of the system’s natural frequencies is initiated when the destabilizing work equals or exceeds the stabilizing work. This approach provides a powerful design tool to quickly ascertain the effects of squeeze-film dampers, and turbine engine architecture, including bearing locations and bearing support structure stiffness, on system stability.
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October 2007
Research Papers
A Simplified Method for Predicting the Stability of Aerodynamically Excited Turbomachinery
Albert F. Storace
Albert F. Storace
Consulting Engineer Dynamics,
Advanced Technology and Preliminary Design
, GE Aviation, Cincinnati, OH
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Albert F. Storace
Consulting Engineer Dynamics,
Advanced Technology and Preliminary Design
, GE Aviation, Cincinnati, OHJ. Turbomach. Oct 2007, 129(4): 724-729 (6 pages)
Published Online: August 29, 2006
Article history
Received:
August 11, 2006
Revised:
August 29, 2006
Citation
Storace, A. F. (August 29, 2006). "A Simplified Method for Predicting the Stability of Aerodynamically Excited Turbomachinery." ASME. J. Turbomach. October 2007; 129(4): 724–729. https://doi.org/10.1115/1.2720870
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