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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Underplatform Dampers for Turbine Blades: Theoretical Modeling, Analysis, and Comparison With Experimental Data

[+] Author and Article Information
K. Y. Sanliturk

Faculty of Mechanical Engineering, Istanbul Technical University, 80191, Gumussuyu, Istanbul, Turkey

D. J. Ewins, A. B. Stanbridge

Mechanical Engineering Department Center of Vibration Engineering, Imperial College of Science, Technology and Medicine, London, SW7 2BX, UK

J. Eng. Gas Turbines Power 123(4), 919-929 (Oct 01, 1998) (11 pages) doi:10.1115/1.1385830 History: Received October 01, 1998
Copyright © 2001 by ASME
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References

Figures

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Schematic illustration of underplatform dampers between adjacent blades
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(a) Typical measured hysteresis loop under constant normal load, (b) representation of measured behavior by an array of macroslip elements
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Platform motion in three-dimensional space. (β is the platform angle, NodeL and NodeR are the platform structural modes.)
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Relative platform displacements
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Relative contact displacements on damper surfaces
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Displacement triangle relating rxy to rL and rR
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Damper displacements with respect to the platform surfaces
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Forces acting on a damper; (a) static case, (b) dynamic case
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Dynamic forces acting on the left platform
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(a) Experimental set-up for simplified blade-damper assembly, (b) finite element model for simplified blade-damper-blade assembly
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(a) Comparison of measured and predicted response levels (directly excited blade), (b) comparison of measured and predicted response levels (indirectly excited blade)
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Initial predictions (damper load=0, 20, 50, 100 N)
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(a) Relative platform motion in radial direction can cause rolling, (b) damper tends to slide if β>tan−1(μ)
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Comparison of measured and predictions after incorporating rolling effect. (Damper load=0, 20, 50, 100 N.)
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Finite element model for the linear part of two-blade assembly
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(a) Correlation of predictions and experimental data. Directly excited blade, Fex=1.0 N, damper load=0, 10, 100, 200 N. (b) Correlation of predictions and experimental data. Indirectly excited blade, Fex=1.0 N, damper load=0, 10, 100, 200 N.

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