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Research Papers: Gas Turbines: Structures and Dynamics

A Methodology for Predicting the Response of Blades With Nonlinear Coatings

[+] Author and Article Information
Sergio Filippi

 GE Aviation, Cincinnati, OH 45246sergio.filippi@ge.com

Peter J. Torvik

 Universal Technology Corporation, Xenia, OH 45385torvikp@asme.org

J. Eng. Gas Turbines Power 133(4), 042503 (Nov 19, 2010) (7 pages) doi:10.1115/1.4002272 History: Received May 27, 2010; Revised June 26, 2010; Published November 19, 2010; Online November 19, 2010

Ceramic coatings applied by air plasma spray or electron beam techniques as thermal barrier coatings or to improve the erosion or corrosion resistance of blades in gas turbine engines are found to add damping to the system. However, such coatings display nonlinear mechanical properties in that the Young’s modulus and the measure of damping are dependent on the amplitude of cyclic strain. To account for the coating nonlinearity, a new methodology for predicting blade response was developed and applied to an actual component coated with a titania-alumina blend ceramic infiltrated with a viscoelastic material. Resonant frequencies, mode shapes, and the forced response of a one blade segment of an integrated disk from a fan stage rotor were computed and compared with results from bench tests. Predicted frequencies agreed satisfactorily with measured values; predicted and observed values of system damping agreed to within 10%. The results of these comparisons are taken to indicate that it is possible to use laboratory-determined material properties together with an iterative finite element analysis to obtain satisfactory predictions of the response of an actual blade with a nonlinear coating.

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Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Room temperature storage modulus (ER) for Ti–Al/NiCrAlY/VEM system

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Figure 2

Room temperature loss modulus (EI) for Ti–Al/NiCrAlY/VEM system

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Figure 3

FEA grid for blade and blisk segment

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Figure 4

Blade response, two-stripe mode; predicted (L), observed (R)

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Figure 5

Blade response, second torsion mode; predicted (L), observed (R)

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Figure 6

Blade response, third flexural mode; predicted (L), observed (R)

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Figure 7

Observed response, first two-stripe mode; velocity (L), phase (R)

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Figure 8

Observed response of coated blade

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Figure 9

Predicted response of blade with 0.51 mm coating at four levels of excitation

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Figure 10

Response near two-stripe resonance for blade with infiltrated ceramic coating. Excitation force=20F.

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