Research Papers

Fluid–Structure Interaction Using a Modal Approach

[+] Author and Article Information
F. Debrabandere

 Numflo, B-7000 Mons, Belgiumfrancois.debrabandere@numflo.eu

B. Tartinville

Numeca International, B-1170 Brussels, Belgiumbenoit.tartinville@numeca.be

Ch. Hirsch

Numeca International, B-1170 Brussels, Belgiumcharles.hirsch@numeca.be

G. Coussement

 Fluid-Machines Department, University of Mons, B-7000 Mons, Belgiumgregory.coussement@umons.ac.be

J. Turbomach 134(5), 051043 (Jun 15, 2012) (6 pages) doi:10.1115/1.4004859 History: Received July 11, 2011; Revised August 02, 2011; Published June 15, 2012; Online June 15, 2012

A new method for fluid‐structure interaction (FSI) predictions is here introduced, based on a reduced-order model (ROM) for the structure, described by its mode shapes and natural frequencies. A linear structure is assumed as well as Rayleigh damping. A two-way coupling between the fluid and the structure is ensured by a loosely coupling staggered approach: the aerodynamic loads computed by the flow solver are used to determine the deformations from the modal equations, which are sent back to the flow solver. The method is first applied to a clamped beam oscillating under the effect of von Karman vortices. The results are compared to a full-order model. Then a flutter application is considered on the AGARD wing 445.6. Finally, the modal approach is applied to the aeroelastic behavior of an axial compressor stage. The influence of passing rotor blade wakes on the downstream stator blades is investigated.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Comparison of numerical results and analytical solution of Eq. 4

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Figure 2

Numerical error induced by the resolution of Eq. 4 and influence of time step size

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Figure 3

Vortex-induced vibration beam

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Figure 4

Instantaneous deformation of the beam at t = 9.8 s

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Figure 5

Tip motion of the beam

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Figure 6

Generalized displacement of the beam

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Figure 7

Mesh used for the AGARD wing 445.6

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Figure 8

Tip motion in lift direction at flutter limit at Mach 0.5

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Figure 9

Flutter speed index of the AGARD wing 445.6

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Figure 10

Frequency ratio of the AGARD wing 445.6

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Figure 11

Geometry and mesh used for the compressor stage

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Figure 12

Absolute Mach number at midspan

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Figure 13

Tip deformation at trailing edges of the stator

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Figure 14

Deformation of stator blades at t = 3.75 × 10−4 s

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Figure 15

Deformation of stator blades at t = 8.9 × 10−4 s

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Figure 16

Fourier transform of the tip motion of the first stator blade



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