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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

A Test Rig for Frictionally Damped Bladed Segments

[+] Author and Article Information
T. Berruti, S. Filippi, L. Goglio, M. M. Gola

Department of Mechanical Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Turin, Italy

S. Salvano

FIAT AVIO, Via Nizza 312, 10127 Turin, Italy

J. Eng. Gas Turbines Power 124(2), 388-394 (Mar 26, 2002) (7 pages) doi:10.1115/1.1419015 History: Received November 01, 1999; Revised February 01, 2000; Online March 26, 2002
Copyright © 2002 by ASME
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References

Srinivasan,  A. V., and Cutts,  D. G., 1984, “Measurement of Relative Vibratory Motion at the Shroud Interfaces of a Fan,” ASME J. Vibr. Acoust., 106, pp. 189–197.
Griffin,  J. H., 1980, “Friction Damping of Resonant Stresses in Gas Turbine Engine Airfoils,” J. Eng. Power, 102, pp. 329–333.
Srinivasan,  A. V., and Cutts,  D. G., 1983, “Dry Friction Damping Mechanisms in Engine Blades,” J. Eng. Power, 105, pp. 332–341.
Berthillier,  M., Dupont,  C., Mondal,  R., and Barrau,  J. J., 1998, “Bladed Force Response—Analysis with Friction Dampers,” ASME J. Vibr. Acoust., 120, pp. 468–474.
Yang,  B. D., and Menq,  C. H., 1998, “Characterization of Contact Kinematics and Application to the Design of Wedge Dampers in Turbomachinery Blading: Part 2—Prediction of Forced Response and Experimental Verification,” ASME J. Eng. Gas Turbines Power, 120, pp. 418–423.
Sanliturk, K. Y., Ewins, D. J., and Stanbridge, A. B., 1999, “Underplatform Dampers for Turbine Blades: Theoretical Modelling, Analysis and Comparison of Experimental Data,” 44th ASME Gas Turbine and Aeroengine Congress and Exhibition, June 7–10, Indianapolis IN, ASME Paper No. 99-GT-335.
Csaba, G., 1999, “Modelling of a Microslip Friction Damper Subjected to Translation and Rotation,” 44th ASME Gas Turbine and Aeroengine Congress and Exhibition, June 7–10, Indianapolis, IN, ASME Paper No. 99-GT-149.
Berruti, T., Filippi, S., Goglio, L., and Gola, M. M., “Forced Vibrations of Frictionally Damped Stator Segments,” 44th ASME Gas Turbine and Aeroengine Congress and Exhibition, June 7–10, Indianapolis, IN, ASME Paper No. 99-GT-412.

Figures

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Stator segment; (a) right side view, (b) left side view, (c) schematics of the assembly
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Sketch of the test rig; (a) top view, (b) detail of the preloading (A, B accelerometer locations)
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Lower platform rotation of a twist angle α
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Sketch of the support instrumented with strain gages
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Support finite element method model
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Sketch of the support calibration; (a) tensile, (b) flexural
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Accelerations measured in hoop direction for the positions A and B of the frame (excitation 1 g pk)
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First mode resonant frequency of the segment versus twist value under different levels of excitation
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Measured time histories of relative hoop displacement normal and tangential contact forces. Twist angle 0.10 angle frequency 165 Hz, excitation 5 g; (a) left support/segment contact, (b) right support/segment contact.
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Measured tangential force versus relative hoop displacement. Twist angle 0.10 deg, frequency 165 Hz, excitation 5 g; (a) left support/segment contact, (b) right support/segment contact.

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