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Research Papers: Gas Turbines: Structures and Dynamics

A Reduced-Order Model of Detuned Cyclic Dynamical Systems With Geometric Modifications Using a Basis of Cyclic Modes

[+] Author and Article Information
Moustapha Mbaye

Laboratoire de Modélisation et Simulation Multi Echelle, Université Paris-Est, MSME FRE3160 CNRS, 5 bd Descartes, 77454 Marne-la-Vallée, France

Christian Soize1

Laboratoire de Modélisation et Simulation Multi Echelle, Université Paris-Est, MSME FRE3160 CNRS, 5 bd Descartes, 77454 Marne-la-Vallée, France

Jean-Philippe Ousty

 Turbomeca—Safran Group, 64511 Bordes, France

1

Corresponding author.

J. Eng. Gas Turbines Power 132(11), 112502 (Aug 10, 2010) (9 pages) doi:10.1115/1.4000805 History: Received May 05, 2009; Revised October 24, 2009; Published August 10, 2010; Online August 10, 2010

A new reduction method for vibration analysis of intentionally mistuned bladed disks is presented. The method is built for solving the dynamic problem of cyclic structures with geometric modifications. It is based on the use of the cyclic modes of the different sectors, which can be obtained from a usual cyclic symmetry modal analysis. Hence the projection basis is constituted; as well as, on the whole bladed disk, each sector matrix is reduced by its own modes. The method is validated numerically on a real bladed disk model, by comparing free and forced responses of a full model finite element analysis to those of a reduced-order model using the new reduction method.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Geometries of twin modes with one nodal diameter obtained by two independent computations: first computation ((a) and (b)) and second computation ((c) and (d))

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Figure 2

Geometries of twin modes with one nodal diameter obtained by two independent computations after phase correction: first computation ((a) and (b)) and second computation ((c) and (d))

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Figure 3

Finite element model of the tuned bladed disk

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Figure 4

Natural frequencies versus circumferential wave numbers of the tuned bladed disk

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Figure 5

Finite element models of blades: a reference blade (a), a light blade (b), and a heavy blade (c)

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Figure 6

Complete intentionally detuned bladed disk with arbitrary geometric modification of two blades

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Figure 7

Comparison of the 76 first detuned eigenfrequencies between the full model and several ROM sizes

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Figure 8

Comparison of the 76 first detuned eigenfrequencies’ prediction errors between the full model and several ROM sizes

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Figure 9

Forced response of the 23 blades to an engine order excitation 5 in the frequency band F: full model (a) and ROM (b)

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Figure 10

Forced response of the 23 blades to an engine order excitation 9 in the frequency band F: full model (a) and ROM (b)

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Figure 11

Comparison of the maximum forced response of the bladed disk obtained with the full and the reduced-order models in the frequency band F: excitation engine order 5 (a) and excitation engine order 9 (b)

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Figure 12

Nominal plate (a) and geometrically modified plate (b)

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Figure 13

Four first modes of the nominal plate: mode 1 (a), mode 2 (b), mode 3 (c), and mode 4 (d)

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Figure 14

Four first modes of the geometrically modified plate: mode 1 (a), mode 2 (b), mode 3 (c), and mode 4 (d)

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