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Research Paper: Gas Turbines: Structures and Dynamics

Forced Response Analysis of a Mistuned Compressor Blisk

[+] Author and Article Information
Bernd Beirow

Mem. ASME
Brandenburg University of Technology,
Siemens-Halske-Ring 14,
Cottbus D-03046, Germany
e-mail: beirow@tu-cottbus.de

Thomas Giersch

Brandenburg University of Technology,
Siemens-Halske-Ring 14,
Cottbus D-03046, Germany
e-mail: thomas.giersch@tu-cottbus.de

Arnold Kühhorn

Mem. ASME
Brandenburg University of Technology,
Siemens-Halske-Ring 14,
Cottbus D-03046, Germany
e-mail: kuehhorn@tu-cottbus.de

Jens Nipkau

Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 4,
Blankenfelde-Mahlow D-15827, Germany
e-mail: Jens.Nipkau@rolls-Royce.com

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received January 9, 2014; final manuscript received January 16, 2014; published online xx xx, xxxx. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(6), 062507 (Feb 11, 2014) (13 pages) Paper No: GTP-14-1008; doi: 10.1115/1.4026537 History: Received January 09, 2014; Revised January 16, 2014

The forced response of an E3E-type high pressure compressor (HPC) blisk front rotor is analyzed with regard to varying mistuning and the consideration of the fluid-structure interaction (FSI). For that purpose, a reduced order model is used in which the disk remains unchanged and mechanical properties of the blades, namely stiffness and damping, are adjusted to measured as well as intentional blade frequency mistuning distributions. The aerodynamic influence coefficient technique is employed to model the aeroelastics. Depending on the blade mode, the exciting engine order, and aerodynamic influences, it is sought for the worst mistuning distributions with respect to the maximum blade displacement based on optimization analyses. Genetic algorithms using blade-alone frequencies as design variables are applied. The validity of the Whitehead limit is assessed in this context. In particular, the question is addressed if and how far aeroelastic effects, mainly caused by aerodynamic damping, combined with mistuning can even cause a reduction of the forced response compared to the ideally tuned blisk. It is shown that the strong dependence of the aerodynamic damping on the interblade phase angle is the main driver for a possible response attenuation considering the fundamental as well as a higher blade mode. Furthermore, the differences to the blisk vibration response without a consideration of the flow and an increase of the disk's stiffness are discussed. Closing, the influence of pure damping mistuning is analyzed again using optimization.

Copyright © 2014 by Rolls-Royce Deutschland Ltd & Co KG
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References

Figures

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Fig. 1

E3E-HPC test-compressor [15]

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Fig. 2

Surrogate blisk model (EBM [17])

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Fig. 3

Blade frequency mistuning patterns (rotational stiffening included)

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Fig. 4

Nodal diameter plot

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Fig. 5

Amplification of maximum blade displacements due to measured mistuning (FSI neglected)

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Fig. 6

Forced response at EO 7 / 1F (FSI neglected)

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Fig. 7

Aerodynamic damping versus IBPA, at MTO

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Fig. 8

Amplification of maximum blade displacements due to measured mistuning (FSI considered)

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Fig. 9

Forced response at EO 7 / 1F (FSI considered)

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Fig. 10

Maximized forced response (FSI not considered)

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Fig. 11

Optimized frequency mistuning patterns according to maximized forced responses (FSI not considered): (a) EO 0 / 1F and (b) EO 7 / 1F

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Fig. 12

Modes of vibration at maximum forced response (FSI not considered): (a) EO 0 / 1F and (b) EO 7 / 1F

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Fig. 13

Maximized forced response at EO 7 / 1F (FSI not considered)

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Fig. 14

Maximized forced response / 1F

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Fig. 15

Resulting aerodynamic damping contribution (1F) normalized to the particular Da,CSM of the tuned blisk

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Fig. 16

(a) Vibration mode / 1F at EO 13 and (b) Fourier decomposition after forced response maximization

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Fig. 17

Minimized forced response / 1F

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Fig. 18

(a) Vibration mode / 1F at EO 3 and (b) Fourier decomposition after forced response minimization

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Fig. 19

Optimized frequency mistuning patterns according to maximized forced responses (FSI considered): (a) EO 0 / 1F and (b) EO 7 / 1F

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Fig. 20

Modes of vibration at maximum forced response (FSI considered): (a) EO 0/1F and (b) EO 7/1F

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Fig. 21

Maximized forced response at EO 7/1F (FSI considered)

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Fig. 22

Average amplification of forced response / 1F (all blades/one EO)

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Fig. 23

Maximized forced response / TL

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Fig. 24

Partial disk displacement at adjacent DOF i in case of maximum displacement at blade-DOF i + 1 / TL

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Fig. 25

Minimized forced response / TL and approximately rigid disk

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Fig. 26

(a) Optimized blade damping mistuning patterns according to maximized forced responses / 1F, (b) forced response

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