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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

Whitehead, D. S., 1966, “Effect of Mistuning on the Vibration of Turbomachine Blades Induced by Wakes,” J. Mech. Eng. Sci., 8(1), pp. 15–21. [CrossRef]
Ewins, D. J., 1969, “The Effects of Detuning Upon the Forced Vibrations of Bladed Disks,” J. Sound Vib., 9(1), pp. 65–79. [CrossRef]
Griffin, J. H., and Hoosac, T. M., 1984, “Model Development and Statistical Investigation of Turbine Blade Mistuning,” ASME J. Vib. Acoust. Stress Reliab. Des., 106(2), pp. 204–210. [CrossRef]
Basu, P., and Griffin, J. H., 1986, “The Effect of Limiting Aerodynamic and Structural Coupling in Models of Mistuned Bladed Disk Vibration,” ASME J. Vib. Acoust. Stress Reliab. Des., 108(2), pp. 132–139. [CrossRef]
Petrov, E. P., and Ewins, D. J., 2003, “Analysis of the Worst Mistuning Patterns in Bladed Disk Assemblies,” ASME J. Turbomach., 125(4), pp. 623–631. [CrossRef]
Judge, J., Pierre, C., and Mehmed, O., 2001, “Experimental Investigation of Mode Localization and Forced Response Amplitude Magnification for a Mistuned Bladed Disk,” ASME J. Eng. Gas Turb. Power, 123(4), pp. 940–950. [CrossRef]
Kenyon, J. A., Griffin, J. H., and Feiner, D. M., 2003, “Maximum Bladed Disk Forced Response From Distortion of a Structural Mode,” ASME J. Turbomach., 125(2), pp 352–363. [CrossRef]
Sever, I. A., 2004, “Experimental Validation of Turbomachinery Blade Vibration Predictions,” Ph.D. thesis, Department of Mechanical Engineering, Imperial College London, London, UK.
Castanier, M. P., and Pierre, C., 2006, “Modelling and Analysis of Mistuned Bladed Disk Vibration: Status and Emerging Directions,” J. Propul. Power, 22(2), pp. 384–396. [CrossRef]
Beirow, B., Kühhorn, A., and Nipkau, J., 2009, “On the Influence of Strain Gauge Instrumentation on Blade Vibrations of Integral Blisk Compressor Rotors Applying a Discrete Model,” ASME Turbo Expo 2009, Orlando, FL, June 8–12, Paper No. GT2009-59207. [CrossRef]
Hönisch, P., Kühhorn, A., and Beirow, B., 2011, “Experimental and Numerical Analyses of Radial Turbine Blisks With Regard to Mistuning,” ASME Turbo Expo 2011, Vancouver, Canada, June 6–11, Paper No. GT2011-45359. [CrossRef]
Petrov, E. P., 2009, “A Method for Forced Response Analysis of Mistuned Bladed Disk With Aerodynamic Effects Included,” ASME Turbo Expo 2009, Orlando, FL, June 8–12, Paper No. GT2009-59634. [CrossRef]
Beirow, B., Kühhorn, A., and Nipkau, J., 2011, “An Equivalent Blisk Model Considering the Influence of the Air Flow on Blade Vibrations of a Mistuned Compressor Blisk,” Vibration Problems ICOVP 2011: The 10th International Conference on Vibration Problems (Springer Proceedings in Physics 139), Springer, Dordrecht, Netherlands, pp. 549–555. [CrossRef]
Nipkau, J., 2010, “Analysis of Mistuned Blisk Vibrations Using a Surrogate Lumped Mass Model With Aerodynamic Influences,” Ph.D. thesis, Brandenburg University of Technology Cottbus, Cottbus, Germany.
Klinger, H., Lazik, W., and Wunderlich, T., 2008, “The Engine 3E Core Engine,” ASME Turbo Expo 2008, Berlin, Germany, June 9–13, Paper No. GT2008-50679. [CrossRef]
Kühhorn, A., and Beirow, B., 2010, “Method for Determining Blade Mistuning on Integrally Manufactured Rotor Wheels,” U.S. Patent No. 2010/0286934 A1.
Beirow, B., Nipkau, J., and Kühhorn, A., 2011, “Modal and Aeroelastic Analysis of a Compressor Blisk Considering Mistuning,” ASME Turbo Expo 2011, Vancouver, Canada, June 6–10, Paper No. GT2011-45849. [CrossRef]
Hanamura, Y., Tanaka, H., and Yamaguchi, K., 1980, “A Simplified Method to Measure Unsteady Forces Acting on the Vibrating Blades in Cascade,” Bull. JSME, 23(180–12), pp. 880–887. [CrossRef]
Kahl, G., 2002, “Aeroelastic Effects of Mistuning and Coupling in Turbomachinery Bladings,” Ph.D. thesis no. 2629, École Polytechnique Fédérale de Lausanne, Lausanne, Switzerland.
Crawley, E. F., and Hall.K. C., 1985, “Optimization and Mechanisms of Mistuning in Cascades,” ASME J. Eng. Gas Turb. Power, 107(2), pp. 418–426. [CrossRef]
Klauke, T., Kühhorn, A., Beirow, B., and Golze, M., 2009, “Numerical Investigations of Localized Vibrations of Mistuned Blade Integrated Disks (Blisks),” ASME J. Turbomach., 131(3), 031002, pp. 1–11. [CrossRef]

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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