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Some Effects of Mechanical Damping on the Self-Induced Aeroelastic Oscillations of an Axial Compressor Blade

Published online by Cambridge University Press:  07 June 2016

I. M. Davidson
I. M. Davidson*
Affiliation:
National Gas Turbine Establishment
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Summary

By a slight modification to den Hartog’s classical theory of harmonically forced vibration off resonance it is shown that, with such distorted forcing wave forms as might be encountered in the stalling or choking flutter of an aerofoil in cascade, the influence of damping on the amplitude of motion can still be assessed with considerable accuracy by the assumption of an equivalent harmonic excitation. The result is valid for any amount of Coulomb damping at which motion is significant in the presence of any “ velocity ” damping coefficient up to that defined by a logarithmic decrement of about 1-3, the formal conclusion of the argument being stated in Section 4.

Type
Research Article
Information
Aeronautical Quarterly , Volume 6 , Issue 2 , May 1955 , pp. 81 - 98
Copyright
Copyright © Royal Aeronautical Society. 1955

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References

1. Bellenot, CH. and Lalive d’epinay, J. Self Induced Vibrations of Turbo-machine Blades. Brown Boveri Review, October 1950.Google Scholar
2. Pearson, H. The Aerodynamics of Compressor Blade Vibration, Fourth Anglo-American Aeronautical Conference, London, 1953. Royal Aeronautical Society, 1954.Google Scholar
3. Den Hartog, J. P. Forced Vibration with Combined Coulomb and Viscous Friction. Transactions of the American Society of Mechanical Engineers, Vol. 53, p. 107, 1931.Google Scholar
4. Kimball, A. L. Vibration Damping, including the Case of Solid Friction. Transactions of the American Society of Mechanical Engineers, Vol 51(1), p. 227, 1929.CrossRefGoogle Scholar