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Research Papers: Gas Turbines: Structures and Dynamics

A Statistical Characterization of the Effects of Mistuning in Multistage Bladed Disks

[+] Author and Article Information
Kiran X. D’Souza

Department of Mechanical Engineering,  University of Michigan, Ann Arbor, MI 48109-2125kdsouza@umich.edu

Bogdan I. Epureanu1

Department of Mechanical Engineering,  University of Michigan, Ann Arbor, MI 48109-2125epureanu@umich.edu

1

Corresponding author.

J. Eng. Gas Turbines Power 134(1), 012503 (Nov 04, 2011) (8 pages) doi:10.1115/1.4004153 History: Received April 14, 2011; Revised April 19, 2011; Published November 04, 2011; Online November 04, 2011

A great deal of research has been conducted on the effects of small random variations in structural properties, known as mistuning, in single stage bladed disks. Due to the inherent randomness of mistuning and the large dimensionality of the models of industrial bladed disks, a reduced order modeling approach is required to understand the effects of mistuning on a particular bladed disk design. Component mode mistuning (CMM) is an efficient compact reduced order modeling method that was developed to handle this challenge in single stage bladed disks. In general, there are multiple stages in bladed disk assemblies, and it has been demonstrated that for certain frequency ranges accurate modeling of the entire bladed disk assembly is required because multistage modes exist. In this work, a statistical characterization of structural mistuning in multistage bladed disks is carried out. The results were obtained using CMM combined with a multistage modeling approach previously developed. In addition to the statistical characterization, a new efficient classification method is detailed for characterizing the properties of a mode. Also, the effects of structural mistuning on the characterization of the mode is explored.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Interstage boundary (b partition) for a cyclic stage (i denotes a sector, k denotes a radial line segment)

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Figure 2

Multistage turbomachinery rotor

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Figure 3

Nodal diameter versus frequency plots for (a) stage 1 and (b) stage 2

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Figure 4

(a) Frequencies of the tuned multistage system, (b) energy ratio in the corresponding modes, and (c) relative frequency difference between the multistage system and the single stage system modes

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Figure 5

(a) Frequencies of the mistuned multistage system and (b) the probability of the classification of the corresponding modes

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Figure 6

Alignment of mistuned multistage modes with tuned multistage modes

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Figure 7

Forced response of stage 2 for a set of stage 2 dominated modes, which are S2 when tuned and MS 2 when mistuned (tuned single stage analysis [x], tuned multistage analysis [—], mistuned single stage analysis [□], and mistuned multistage analysis […])

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Figure 8

Forced response for a set of S1, MS 1 , and M1,2 modes for (a) stage 1 and (b) stage 2 (tuned single stage analysis [x], tuned multistage analysis [—], mistuned single stage analysis [□], and mistuned multistage analysis […])

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Figure 9

MAC number versus mistuning level for (a) mode 36 [S1, MS 1 ] and (b) mode 6 [S2, MS 2 ] (error bars indicate the standard deviation of these values for 100 mistuning patterns)

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Figure 10

Force amplification factor versus mistuning level and engine order excitation for the multistage system for (a) stage 1 and (b) stage 2

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Figure 11

Maximum force response versus mistuning level and engine order excitation for the multistage system for (a) stage 1 and (b) stage 2

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