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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Application of Model Order Reduction to Compressor Aeroelastic Models

[+] Author and Article Information
K. Willcox, J. Peraire, J. D. Paduano

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Eng. Gas Turbines Power 124(2), 332-339 (Mar 26, 2002) (8 pages) doi:10.1115/1.1416152 History: Received November 01, 1999; Revised February 01, 2000; Online March 26, 2002
Copyright © 2002 by ASME
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References

Figures

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DFVLR transonic rotor from Youngren 11 and steady pressure coefficient profile computation compared to data from Schreiber and Starken 12
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Low-speed airfoil cross sections from Silkowski 13, shown for one quarter of the computational domain used for stage analysis. Arrows represent the characteristics waves: entropy wave (s), vorticity wave (ζ), and downstream and upstream running pressure waves (P+ and P−).
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Unsteady aerodynamic plunge force on the DFVLR transonic rotor, computed at several reduced frequencies (symbols) and plotted against reduced-order model results (solid lines). Dashed lines show assumed frequency predictions, which are constant with frequency.
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Comparison of eigenvalues obtained using reduced-order model and assumed-frequency method
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Comparison of damping and frequency of eigenvalues obtained using reduced-order model and assumed-frequency method
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Displacement response of the transonic rotor to excitation over a broad range of reduced frequencies
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Aerodynamic force on blade 1 of the low-speed rotor due to a prescribed pulse input on its plunge displacement. Blades are considered rigid for this run.
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Force on every blade of low-speed rotor due to an initial displacement of the coupled system. The structure and aerodynamics are coupled in this run. Solid—with stator, dashed—no stator.
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Eigenvalues of the low-speed rotor. Eigenvalues are numbered by their nodal diameter (σ=2π1/16).

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