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Research Papers

Reduced Order Model of a Multistage Bladed Rotor With Geometric Mistuning via Modal Analyses of Finite Element Sectors

[+] Author and Article Information
Yasharth Bhartiya

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, University Park, PA 16802yasharth@gmail.com

Alok Sinha

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, University Park, PA 16802axs22@psu.edu

J. Turbomach 134(4), 041001 (Jul 19, 2011) (8 pages) doi:10.1115/1.4003224 History: Received July 14, 2010; Revised September 30, 2010; Published July 19, 2011; Online July 19, 2011

An algorithm to generate a reduced order model of a multistage rotor in which each stage has a different number of blades has been developed. It is shown that a reduced order model can be developed on the basis of tuned modes of certain bladed disks which can be easily obtained via sector analyses. Further, it is shown that the reduced order model can also be obtained when blades are geometrically mistuned. This algorithm is similar to the modified modal domain analysis, which has been recently developed for a single-stage bladed rotor with geometric mistuning. The validity of this algorithm is shown for the finite element model of a two-stage bladed rotor. In addition, the statistical distributions of peak maximum amplitudes and natural frequencies of a two-stage rotor are generated via Monte Carlo simulations for different patterns of geometric mistuning.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

A two-stage rotor

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Figure 2

(a) Connecting ring attached to left disk and (b) connecting ring attached to right disk

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Figure 3

Error (%) in frequency estimated via reduced order model (tuned two-stage rotor, r=q=120)

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Figure 4

Difference between modal vectors (mode no. 1 and mode no. 4) from reduced order model and full rotor ANSYS analysis (tuned two-stage rotor, r=q=120)

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Figure 5

Error (%) in frequency estimated via reduced order model (tuned two-stage rotor, r=24 and q=20)

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Figure 6

Error (%) in frequency estimated via reduced order model (tuned two-stage rotor, r=48 and q=40)

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Figure 7

Difference between modal vectors (mode no. 1 and mode no. 4) from reduced order model and ANSYS analysis, (r=48 and q=40)

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Figure 8

Mistuning pattern for Disk1 and Disk2

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Figure 9

Deviations in natural frequencies of a mistuned two-stage rotor (r=q=120)

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Figure 10

Errors (%) in deviations of natural frequencies from tuned two-stage rotor (r=q=120)

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Figure 11

Difference between mistuned modal vectors (mode no. 1 and mode no. 3) from reduced order model and full ANSYS analysis (r=q=120)

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Figure 12

Blade tip amplitude of Disk1 (top) and Disk2 (bottom) as a function of excitation frequencies (r=q=120)

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Figure 13

Forced responses of single-stage and multistage rotors (engine order 2, mean forcing frequency=4102 Hz) (r=q=120)

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Figure 14

Mistuning pattern of a random permutation of blades

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Figure 15

Deviations in natural frequencies of a mistuned two-stage rotor (r=48 and q=40)

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Figure 16

Distribution of first natural frequency (r=48 and q=40)

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Figure 17

Distribution of 21st natural frequency (r=48 and q=40)

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Figure 18

Distribution of 41st natural frequency (r=48 and q=40)

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Figure 19

Peak maximum amplitude distribution for harmonic force applied to Disk1 (r=48 and q=40)

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