A shock spectrum procedure is developed to estimate the peak displacement response of linear flexible rotor-bearing systems subjected to a step change in unbalance (i.e., a blade loss). A progressive and a retrograde response spectrum are established. These blade loss response spectra are expressed in a unique non-dimensional form and are functions of the modal damping ratio and the ratio of rotor spin speed to modal damped whirl speed. Modal decomposition using complex modes is utilized to make use of the unique feature of the spectra for the calculation of the peak blade loss displacement response of the rotor system. The procedure is applied to three example systems using several modal superposition strategies. The results of each are compared to true peak displacements obtained by a separate transient response program.
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January 1985
Research Papers
A Blade Loss Response Spectrum for Flexible Rotor Systems
M. Alam,
M. Alam
Mechanical and Aerospace Engineering, Arizona State University, Tempe, Ariz. 85287
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H. D. Nelson
H. D. Nelson
Mechanical and Aerospace Engineering, Arizona State University, Tempe, Ariz. 85287
Search for other works by this author on:
M. Alam
Mechanical and Aerospace Engineering, Arizona State University, Tempe, Ariz. 85287
H. D. Nelson
Mechanical and Aerospace Engineering, Arizona State University, Tempe, Ariz. 85287
J. Eng. Gas Turbines Power. Jan 1985, 107(1): 197-204 (8 pages)
Published Online: January 1, 1985
Article history
Received:
December 19, 1983
Online:
October 15, 2009
Citation
Alam, M., and Nelson, H. D. (January 1, 1985). "A Blade Loss Response Spectrum for Flexible Rotor Systems." ASME. J. Eng. Gas Turbines Power. January 1985; 107(1): 197–204. https://doi.org/10.1115/1.3239683
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Bearing Dynamic Coefficients in Rotordynamics: Computation Methods and Practical Applications