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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Dynamic Response Predictions for a Mistuned Industrial Turbomachinery Rotor Using Reduced-Order Modeling

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

M. P. Castanier

Department of Mechanical Engineering, The University of Michigan, Ann Arbor, MI 48109-2125

M. J. Kruse

Honeywell Engines & Systems, Product Safety & Integrity, M/S 2101-121, Phoenix, AZ 85034-3440

J. Eng. Gas Turbines Power 124(2), 311-324 (Mar 26, 2002) (14 pages) doi:10.1115/1.1447236 History: Received October 01, 2000; Revised August 01, 2001; Online March 26, 2002
Copyright © 2002 by ASME
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References

Figures

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Finite element meshes for the industrial 29-blade compressor rotor: (a) the full model; (b) the fundamental sector
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Employed component modes: (a) normal modes of a cantilevered blade; (b) cyclic modes for a fundamental disk-blade sector, where the blade is massless
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Natural frequencies versus number of nodal diameters for the tuned rotor by finite element and reduced-order modeling
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Comparison of tuned finite element and ROM four nodal diameter mode shapes (dominated by 1F motion)
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Comparison of tuned finite element and ROM one nodal diameter mode shapes (dominated by 2F motion). This mode is located in the investigated veering.
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Comparison of mistuned finite element and ROM mode shapes in the frequency region encompassing the 1F blade-dominated modes. The mode shape is spatially localized about blade number six.
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Comparison of mistuned finite element and ROM mode shapes in the frequency region encompassing the investigated veering. Motion is dominated by the 2F blade mode and is localized about blade number six.
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Comparison of tuned finite element and ROM forced responses, for blade tip excitation with C=4
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Comparison of mistuned finite element and ROM maximum blade forced responses, for blade tip excitation with C=4
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Comparison of tuned finite element and ROM forced responses, for blade tip excitation with C=1
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Comparison of mistuned finite element and ROM maximum blade forced responses, for blade tip excitation with C=1
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Histogram of the maximum blade response amplitudes for engine order one excitation. Obtained by Monte Carlo simulation of 1000 different mistuned systems with uniform distributions of zero mean and three percent standard deviation.
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Comparison of Weibull and Monte Carlo determined responses for 5th, 50th, and 95th percentiles of maximum blade response amplitude magnification. The approximate percentiles from the Weibull distributions conform well with the Monte Carlo percentiles.
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Comparison of Weibull estimates of the probability density function for several sets of 50 mistuning patterns each and the full set of 1000 mistuning patterns. The Weibull approximations based on the smaller sets conform well with the probability density function obtained with the full set.
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Variation in blade amplitude magnification factor with standard deviation of mistuning. Mistuned maximum principal stresses are as much as 86 percent higher than the tuned maximum principal stress.
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Definition of index notation
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Natural frequencies versus number of nodal diameters as a continuous variable
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Close-up view of intense frequency veering region in Fig. 17
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Finite difference approximation of curvature for mode sets 4 and 5
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Forced response statistical data for selected frequency veerings

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