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Research Papers: Gas Turbines: Structures and Dynamics

Forced Response Analysis of High-Mode Vibrations for Mistuned Bladed Disks With Effective Reduced-Order Models

[+] Author and Article Information
Yongliang Duan

College of Energy and Power Engineering,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: tracy_duan@nuaa.edu.cn

Chaoping Zang

College of Energy and Power Engineering,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: c.zang@nuaa.edu.cn

E. P. Petrov

School of Engineering and Informatics,
University of Sussex,
Brighton BN1 9QT, UK
e-mail: y.petrov@sussex.ac.uk

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 1, 2016; final manuscript received April 27, 2016; published online June 1, 2016. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(11), 112502 (Jun 01, 2016) (12 pages) Paper No: GTP-16-1120; doi: 10.1115/1.4033513 History: Received April 01, 2016; Revised April 27, 2016

This paper is focused on the analysis of effects of mistuning on the forced response of gas turbine engine bladed disks vibrating in the frequency ranges corresponding to higher modes. For high modes considered here, the blade aerofoils are deformed during vibrations and the blade mode shapes differ significantly from beam mode shapes. A model reduction technique is developed for the computationally efficient and accurate analysis of forced response for bladed disks vibrating in high-frequency ranges. The high-fidelity finite element (FE) model of a tuned bladed disk sector is used to provide primary information about dynamic properties of a bladed disk, and the blade mistuning is modeled by specially defined mistuning matrices. The forced response displacement and stress amplitude levels are studied. The effects of different types of mistuning are examined, and the existence of high amplifications of mistuned forced response levels is shown for high-mode vibrations: in some cases, the resonance peak response of a tuned structure can be lower than out-of-resonance amplitudes of its mistuned counterpart.

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References

Figures

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Fig. 1

A tuned bladed disk: (a) a whole bladed disk and (b) a sector

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Fig. 9

Normalized forced response excited by 15EO: (a) bladed disk maximum response and (b) maximum blade amplitudes

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Fig. 10

Normalized forced response excited by 6EO: (a) bladed disk maximum response and (b) maximum blade amplitudes

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Fig. 2

Selection of narrow frequency ranges for resonance response calculation

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Fig. 3

Maximum resonance amplitudes for all the blades

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Fig. 4

Natural frequencies of the tuned bladed disk

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Fig. 5

Mode shapes of alone blade: (a) sixth mode, (b) seventh mode, and (c) eighth mode

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Fig. 6

Mistuning element distributions: (a) applied to all the nodes, (b) uniform distribution along blade length, (c) linear distribution along blade length, and (d) based on mode shapes

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Fig. 7

First 12 natural frequencies mistuning for different element distributions when the sixth mode has ± 5% frequency mistuning

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Fig. 8

Results of the validation: (a) errors in natural frequency determination and (b) the maximum amplitudes

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Fig. 11

Tuned modes contributions to maximum forced response of the mistuned system: (a) 15EO and (b) 6EO

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Fig. 12

Von Mises stress distribution for 15EO: (a) a whole bladed disk and (b) a zoomed view of blades with highest stresses

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Fig. 13

Von Mises stress distribution for 6EO: (a) a whole bladed disk and (b) a zoomed view of blades with highest stresses

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Fig. 14

Stress and displacement amplification factors for each blade at maximum resonance: (a) 15EO and (b) 6EO

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Fig. 15

Maximum normalized response for mistuned and tuned bladed disks excited by 15EO

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Fig. 16

Maximum normalized response for mistuned and tuned bladed disks excited by 6EO

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Fig. 21

Maximum forced response for mistuned and tuned bladed disks in other high modes: (a) 5EO and (b) 11EO

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Fig. 17

Maximum normalized response for each blade in the frequency range excited by 15EO

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Fig. 18

Maximum normalized response for each blade in the frequency range excited by 6EO

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Fig. 19

Maximum forced response for mistuned and tuned bladed disks: (a) 2EO and (b) 7EO

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Fig. 20

Maximum normalized response in different high-frequency ranges under different EO excitations

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Fig. 22

Statistical distribution of amplification factors for different EOs: (a) 6EO and (b) 15EO

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Fig. 23

Best-fit cumulative distribution function for normalized response under different EO excitations

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