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Research Papers

Intentional Response Reduction by Harmonic Mistuning of Bladed Disks With Aerodynamic Damping

[+] Author and Article Information
Sebastian Willeke

Institute of Dynamics and Vibration Research,
Leibniz University,
Hannover 30167, Germany
e-mail: willeke@ids.uni-hannover.de

Lukas Schwerdt

Institute of Dynamics and Vibration Research
Leibniz University,
Hannover 30167, Germany
e-mail: schwerdt@ids.uni-hannover.de

Lars Panning-von Scheidt

Institute of Dynamics and Vibration Research,
Leibniz University,
Hannover 30167, Germany
e-mail: panning@ids.uni-hannover.de

Jörg Wallaschek

Institute of Dynamics and Vibration Research,
Leibniz University,
Hannover 30167, Germany
e-mail: wallaschek@ids.uni-hannover.de

1Corresponding author.

Manuscript received June 22, 2018; final manuscript received July 2, 2018; published online October 24, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 140(12), 121010 (Oct 24, 2018) (10 pages) Paper No: GTP-18-1292; doi: 10.1115/1.4040898 History: Received June 22, 2018; Revised July 02, 2018

A harmonic mistuning concept for bladed disks is analyzed in order to intentionally reduce the forced response of specific modes below their tuned amplitude level. By splitting a mode pair associated with a specific nodal diameter pattern, the lightly damped traveling wave mode of the nominally tuned blisk is superposed with its counter-rotating complement. Consequently, a standing wave is formed in which the former wave train benefits from an increase in aerodynamic damping. Unlike previous analyses of randomly perturbed configurations, the mode-specific stabilization is intentionally promoted through adjusting the harmonic content of the mistuning pattern (MT). Through a reorientation of the localized mode shapes in relation to the discrete blades, the response is additionally attenuated by an amount of up to 7.6%. The achievable level of amplitude reduction is analytically predicted based on the properties of the tuned system. Furthermore, the required degree of mistuning for a sufficient separation of a mode pair is derived.

Copyright © 2018 by ASME
Topics: Damping , Disks , Blades
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References

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Figures

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Fig. 1

Magnitude of the aerodynamic influence coefficients for the reference blade 0

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Fig. 2

Evolution of the maximum response with and without aerodynamic damping (p = 2)

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Fig. 3

Lumped parameter model of a bladed disk with aerodynamic influence on a single blade

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Fig. 5

EO1-response in the blade-to-blade (top) and modal domain (bottom) for various degrees of mistuning (p = 2): (a)response amplitude of each blade, (b) interblade phase angle, (c) response amplitude of mode pair, and (d) modal phase difference of mode pair

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Fig. 4

Splitting of a natural frequency pair with increasing mistuning strength

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Fig. 6

Evolution of the EO1-response for various mistuning orientations in vacuum (p = 2)

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Fig. 7

Discretized MT, mode shapes (M1, M2), and maximum DS for various mistuning orientations

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Fig. 15

Maximum response in the limiting case for various mistuning orientations (p = 2EO)

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Fig. 8

Monoharmonic and multiharmonic mistuning patterns with eight blades

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Fig. 9

Evolution of the maximum response for various mono- and multiharmonic contents

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Fig. 10

Response in the limiting case for various mistuning orientations in vacuum (p = 2EO)

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Fig. 11

Response sensitivity for various mistuning orientations in the limiting case (ND1-mode pair)

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Fig. 12

Sensitivity of frequency splitting for various harmonic contents (ND1-mode pair)

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Fig. 13

Generic aerodynamic damping of the lumped parameter model

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Fig. 14

Evolution of the maximum response for various mistuning orientations (p = 2)

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Fig. 16

Nodal diameter diagram and finite element model of the bladed disk sector

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Fig. 17

Aerodynamic damping of the blisk (LINSUB simulation)

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Fig. 18

Evolution of the maximum blisk response for various mistuning orientations (p = 2)

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Fig. 19

Maximum blisk response in the limiting case for various mistuning orientations (p = 2EO)

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