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Research Papers: Gas Turbines: Structures and Dynamics

Analysis of Forced Response for Bladed Disks Mistuned by Material Anisotropy Orientation Scatters

[+] Author and Article Information
Chaoping Zang

Jiangsu Province Key Laboratory of
Aerospace Power System,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: c.zang@nuaa.edu.cn

Yuanqiu Tan

Jiangsu Province Key Laboratory of
Aerospace Power System,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: y.tan@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 October 16, 2016; final manuscript received July 7, 2017; published online October 10, 2017. Assoc. Editor: Alexandrina Untaroiu.

J. Eng. Gas Turbines Power 140(2), 022503 (Oct 10, 2017) (12 pages) Paper No: GTP-16-1501; doi: 10.1115/1.4037863 History: Received October 16, 2016; Revised July 07, 2017

A new method is developed for the forced response analysis of mistuned bladed disks manufactured from anisotropic materials and mistuned by different orientations of material anisotropy axes. The method uses (i) sector finite element (FE) models of anisotropic bladed disks and (ii) FE models of single blades and allows the calculation of displacements and stresses in a mistuned assembly. A high-fidelity reduction approach is proposed which ensures high-accuracy modeling by introducing an enhanced reduction basis. The reduction basis includes the modal properties of specially selected blades and bladed disks. The technique for the choice of the reduction basis has been developed, which provides the required accuracy while keeping the computation expense acceptable. An approach for effective modeling of anisotropy-mistuned bladed disk without a need to create a FE model for each mistuning pattern is developed. The approach is aimed at fast statistical analysis based on Monte Carlo simulations. All components of the methodology for anisotropy-mistuned bladed disks are demonstrated on the analysis of models of practical bladed disks. Effects of anisotropy mistuning on forced response levels are explored.

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References

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Figures

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Fig. 1

Material (x, y, z) and blade (X, Y, Z) CSs

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Fig. 2

Plan visualization of primary axis position

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Fig. 4

Finite element model: (a) a bladed disk and (b) a sector

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Fig. 5

Natural frequencies of the tuned bladed disk

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Fig. 6

Primary axis distributions of a random pattern

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Fig. 7

Natural frequency comparison of turbine bladed disk

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Fig. 8

Errors in first 384 natural frequencies

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Fig. 9

Maximum amplitude comparisons: excited by 22EO

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Fig. 10

Maximum amplitude distribution on blades: excited by 22EO

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Fig. 11

Normalized forced responses for each blade: excited by 2EO

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Fig. 12

Normalized forced response of bladed disk maximum amplitude excited by 2EO

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Fig. 13

Normalized forced response of bladed disk maximum amplitude excited by 22EO

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Fig. 14

Normalized maximum forced response of bladed disk in high mode and excited by 2EO

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Fig. 15

Normalized maximum forced response of bladed disk in high mode and excited by 22EO

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Fig. 16

Dependence of the maximum normalized amplitude on the range of anisotropy primary angle

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Fig. 17

von Mises stress distribution of mistuned bladed disk excited by 2EO: (a) the whole model and (b) a zoomed view of blades with highest stress levels

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Fig. 18

von Mises stress distribution of mistuned bladed disk excited by 22EO: (a) the whole model and (b) a zoomed view of blades with highest stress levels

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Fig. 19

Errors of blades maximum amplitude varied with respect to partition number of first Eulerian angle: Nθ=11

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Fig. 20

Errors of blades maximum amplitude varied with respect to partition number of second Eulerian angle: Nψ=36

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Fig. 21

Errors of natural frequencies obtained from condensed matrix solved directly and approximately

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Fig. 22

Statistical distribution of amplification factor: (a) 2EO and (b) 22EO

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