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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Optimization of Intentional Mistuning Patterns for the Reduction of the Forced Response Effects of Unintentional Mistuning: Formulation and Assessment

[+] Author and Article Information
B.-K. Choi

School of Mechanical and Aerospace Engineering, The Institute of Marine Industry, Gyeongsang National University, Tongyoung, Kyongnam 650-160, Korea

J. Lentz

Honeywell Engines and Systems, Department 93-31/301-125, P.O. BOX 52181, Phoenix, AZ 85072-2181

A. J. Rivas-Guerra, M. P. Mignolet

Department of Mechanical and Aerospace Engineering, Arizona State University, Tempe, AZ 85287-6106

J. Eng. Gas Turbines Power 125(1), 131-140 (Dec 27, 2002) (10 pages) doi:10.1115/1.1498270 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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Graphical description of the single-point crossover technique
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Single-degree-of-freedom per blade disk model
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Convergence plot of the simple genetic algorithm, single-degree-of-freedom model, kC=8,606 N/m
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Amplification factor of the forced response with respect to the tuned disk as a function of the level of unintentional mistuning, single-degree-of-freedom model, kC=45,430 N/m. Blades C are tuned, A and B have natural frequencies 5% lower and higher, respectively, than tuned. The notation 3A3B refers to disks formed of two groupings AAABBB or (AAABBB)2 and similarly 2B1A represents (BBA)4.
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Amplification factor of the forced response with respect to the tuned disk as a function of the level of unintentional mistuning, single-degree-of-freedom model, kC=8,606 N/m. Blades C are tuned, A and B have natural frequencies 5% lower and higher, respectively, than tuned. The notation 2A2B refers to disks formed of three groupings AABB or (AABB)3 and similarly 2B1A represents (BBA)4.
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Typical APU load compressor with inlet guide vanes
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Single sector structural model of the 17-blade centrifugal compressor rotor
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Natural frequencies versus number of nodal diameters for the tuned rotor in Fig. 7 by finite element and ROM
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Scatter plot of the width of partial mistuning required to achieve an accuracy of 10% on the amplitude of response of the blades of ten randomly mistuned 2B1A disks, kC=8606 N/m
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Scatter plot of the width of partial mistuning required to achieve an accuracy of 10% on the amplitude of response of the blades of ten randomly mistuned 2B2A disks, kC=8606 N/m
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Scatter plot of the width of partial mistuning required to achieve an accuracy of 10% on the amplitude of response of the blades of 2B1A and 7A5B disks, kC=45,430 N/m, no random mistuning
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Sensitivity of the tuned and optimized intentionally mistuned disks to unintentional random mistuning
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Sensitivity of the optimized and some harmonically intentionally mistuned disks to unintentional random mistuning
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Scatter plot of the width of partial mistuning required to achieve an accuracy of 10% on the amplitude of response of the blades of 2B1A and 2B2A disks, kC=8606 N/m, no random mistuning
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Complex mode shape of the compressor disk for a nodal diameter 3 mode
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Amplitude magnification for the nominal and intentionally mistuned rotors
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Typical convergence plot of the combination of subproblem approximation and steepest descent algorithms

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