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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Effects of Multistage Coupling and Disk Flexibility on Mistuned Bladed Disk Dynamics

[+] Author and Article Information
R. Bladh, M. P. Castanier, C. Pierre

Department of Mechanical Engineering, The University of Michigan, 2250 G. G. Brown Building, Ann Arbor, MI 48109-2125

J. Eng. Gas Turbines Power 125(1), 121-130 (Dec 27, 2002) (10 pages) doi:10.1115/1.1498267 History: Received December 01, 2000; Revised March 01, 2001; Online December 27, 2002
Copyright © 2003 by ASME
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References

Figures

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Finite element meshes for the single and two-stage example rotor models
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Employed random blade mistuning patterns
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Deformed finite element shapes for (a) a blade-dominated mode and (b) a disk-dominated mode, which are both confined to stage 2 (lower stage)
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Stage 1 strain energies relative to total multistage strain energies for “tuned” and blade mistuned multistage modes below 8000 Hz
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Deformed finite element shapes for (a) a multistage system mode and (b) a mixed disk-blade mode confined to stage 1 (upper stage)
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Natural frequencies versus number of nodal diameters for the tuned stage 1 model with fixed interstage boundaries, and for the “tuned” multistage model for modes confined to stage 1
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Natural frequencies versus number of nodal diameters for the tuned stage 2 model with fixed interstage boundaries, and for the “tuned” multistage model for modes confined to stage 2
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“Tuned” multistage mode shapes 54 and 83
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Mistuned single and multistage mode shapes 54 and 83
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Stage 1 forced response from engine order 10 excitation (10EO=−2EO), using tuned and mistuned finite element single and multistage models
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Stage 2 forced response from engine order 15 excitation (15EO=−1EO), using tuned and mistuned finite element single and multistage models
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Detailed view over the stage 1 eigenfrequency veering region indicated in Fig. 6 (single-stage) using a pseudo-continuous interblade phase angle description for varying levels of disk Young’s modulus (E)
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Upper and lower eigenfrequency curvatures in the stage 1 veering region depicted in Fig. 12 for varying levels of disk Young’s modulus (E)
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Tuned stage 1 forced response from engine order 10 excitation (10EO=−2EO) using the single-stage finite element model for varying levels of disk Young’s modulus (E)
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Mistuned stage 1 forced response from engine order 10 excitation (10EO=−2EO) using the single-stage finite element model for varying levels of disk Young’s modulus (E)
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Maximum tuned and mistuned stage 1 forced responses from engine order 10 excitation (10EO=−2EO) as a function of disk Young’s modulus (E) using the single-stage finite element model
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Mistuned stage 1 response amplification from engine order 10 excitation (10EO=−2EO) and local eigenfrequency veering characteristics as functions of disk Young’s modulus (E)
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Natural frequencies versus number of nodal diameters for the tuned stage 1 rotor model using different interstage boundary conditions, plus identified harmonics of the “tuned” two-stage model
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Detailed view of the eigenfrequency veering region indicated in Fig. 18
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Stage 1 tuned finite element forced responses from engine order 10 excitation (10EO=−2EO) using different interstage boundary conditions, plus the “tuned” multistage finite element response
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Stage 1 mistuned finite element forced responses from engine order 10 excitation (10EO=−2EO) using different interstage boundary conditions, plus the blade mistuned multistage finite element response
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Detailed view of the indicated eigenfrequency veering region (upper left) for the tuned stage 1 rotor model using different interstage boundary conditions, plus identified harmonics of the “tuned” two-stage model, with a fourfold increase of Young’s modulus in disks and interstage rims
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Stage 1 tuned finite element forced responses from engine order 11 excitation (11EO=−1EO) using different interstage boundary conditions, plus the “tuned” multistage finite element response, with a fourfold increase of Young’s modulus in disks and interstage rims
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Detailed view of the indicated eigenfrequency veering region (upper left) for the tuned stage 1 rotor model using different interstage boundary conditions, plus identified harmonics of the “tuned” two-stage model, with a fourfold increase of Young’s modulus in disks alone
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Stage 1 tuned finite element forced responses from engine order 11 excitation (11EO=−1EO) using different interstage boundary conditions, plus the “tuned” multistage finite element response, with a fourfold increase of Young’s modulus in disks alone

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