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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics and Aircraft Engines

Computation of the Optimal Normal Load of a Friction Damper Under Different Types of Excitation

[+] Author and Article Information
D. Cha, A. Sinha

Department of Mechanical Engineering, The Pennsylvania State University, University Park, PA 16802

J. Eng. Gas Turbines Power 125(4), 1042-1049 (Nov 18, 2003) (8 pages) doi:10.1115/1.1584474 History: Received October 01, 1998; Revised March 01, 1999; Online November 18, 2003
Copyright © 2003 by ASME
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References

Griffin,  J. H., 1980, “Friction Damping of Resonant Stresses in Gas Turbine Engine Airfoils,” ASME J. Eng. Gas Turbines Power, 102, pp. 329–333.
Srinivasan,  A. V., and Cutts,  D. G., 1983, “Dry Friction Damping Mechanisms in Engine Blades,” ASME J. Eng. Gas Turbines Power, 105, pp. 332–341.
Menq,  C.-H., Griffin,  J. H., and Bielak,  J., 1986, “The Influence of a Variable Normal Load on the Forced Vibration of a Frictionally Damped Structure,” ASME J. Eng. Gas Turbines Power, 108, pp. 300–305.
Cameron,  T. M., Griffin,  J. H., Kielb,  R. E., and Hoosac,  T. M., 1990, “An Integrated Approach for Friction Damper Design,” ASME J. Vibr. Acoust., 112, pp. 175–182.
Sanliturk,  K. Y., Imregun,  M., and Ewins,  D. J., 1997, “Harmonic Balance Vibration Analysis of Turbine Blades With Friction Dampers,” ASME J. Vibr. Acoust., 119, pp. 96–103.
Asano,  K., and Iwan,  W. D., 1984, “An Alternative Approach to the Random Response of Bilinear Hysteretic Systems,” J. Earthquake Eng. Struct. Dyn.,12, pp. 229–236.
Sinha,  A., 1990, “Friction Damping of Random Vibration in Gas Turbine Engine Airfoils,” International Journal of Turbo and Jet Engines, 7 , pp. 95–102.
Roberts, J. B., and Spanos, P. D., 1990, Random Vibration and Statistical Linearization, Chichester: John Wiley and Sons, Chichester.
Whitehead, D. S., 1960, “The Analysis of Blade Vibration due to Random Excitation,” Reports and Memoranda R & M 3253, Cambridge University, Cambridge, UK.
Sogliero,  G., and Srinivasan,  A. V., 1980, “Fatigue Life Estimates of Mistuned Blades via a Stochastic Approach,” AIAA J., 18(83), pp. 318–323.
Minkiewicz, G., and Russler, P., 1997, “Dynamic Response of Low Aspect Ratio Blades in a Two Stage Transonic Compressor,” AIAA Paper No. 97-3284.
Chen,  S., and Sinha,  A., 1990, “Probabilistic Method to Compute the Optimal Slip Load for a Mistuned Bladed Disk Assembly With Friction Dampers,” ASME J. Vibr. Acoust., 112, pp. 214–221.
Socha,  L., and Soong,  T. T., 1991, “Linearization in Analysis of Nonlinear Stochastic Systems,” Appl. Mech. Rev., 44, pp. 399–422.
Griffin,  J. H., and Sinha,  A., 1985, “The Interaction Between Mistuning and Friction in the Forced Response of Bladed Disk Assemblies,” ASME J. Eng. Gas Turbines Power, 107, pp. 205–211.
MATLAB Manual, 1995, The MathWorks, Inc.
Deo, N., 1980, System Simulation With Digital Computer, Prentice-Hall, Englewood Cliffs, NJ, pp. 153–154.

Figures

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A blade-to-ground damper
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Equivalent single-degree-of-freedom system
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Hysteretic characteristic of a friction damper (sinusoidal response)
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Ap as a function of xc (sinusoidal excitation)
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Rx as a function of xc (white noise excitation)
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(a) Rx as a function of xc and ωF (narrowband excitation); (b) peak value of Rx as a function of xc (narrowband excitation)
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(a) σx/Q0 as a function of μfFN/Q0 (W.N.); (b) peak value of σx/Q0 as a function of μfFN/Q0 (N.B.); (c) Ap/f0 as a function of μfFN/f0 (S.)
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σxst versus xcst for white noise excitation, peak value of σxst versus xcst for narrow band excitation, rms(xp)/rms(xst) versus xc/rms(xst) for sinusoidal excitation (KG=43,000 N/m)
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σxst versus xcst for white noise excitation, peak value of σxst versus xcst for narrow band excitation, rms(xp)/rms(xst) versus xc/rms(xst) for sinusoidal excitation, (KG=64,500 N/m)
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Peak value of σxst versus xcstF=0.01, 0.05, and 0.1)

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