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Research Papers

Analysis of Flutter-Induced Limit Cycle Oscillations in Gas-Turbine Structures With Friction, Gap, and Other Nonlinear Contact Interfaces

[+] Author and Article Information
E. P. Petrov

 Mechanical Engineering Department,Centre of Vibration Engineering, Imperial College London, South Kensington Campus, London, SW7 2AZ, UKy.petrov@imperial.ac.uk

J. Turbomach 134(6), 061018 (Sep 04, 2012) (13 pages) doi:10.1115/1.4006292 History: Received June 20, 2011; Revised July 22, 2011; Published September 04, 2012; Online September 04, 2012

A frequency-domain method has been developed to predict and comprehensively analyze the limit-cycle flutter-induced vibrations in bladed disks and other structures with nonlinear contact interfaces. The method allows, for the first time, direct calculation of the limit-cycle amplitudes and frequencies as functions of contact interface parameters and aerodynamic characteristics using realistic large-scale finite element models of structures. The effects of the parameters of nonlinear contact interfaces on limit-cycle amplitudes and frequencies have been explored for major types of nonlinearities occurring in gas-turbine structures. New mechanisms of limiting the flutter-induced vibrations have been revealed and explained.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 5

Dependency of LCO frequency and amplitudes on friction coefficient and the normal load

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Figure 6

Time domain LCO solutions obtained for different normal load values

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Figure 7

Dependency of LCO frequency and amplitudes on tangential stiffness of the friction damper kt

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Figure 8

LCO solutions obtained in time domain: (a) for kt=104 from different initial conditions (b) for kt=200

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Figure 9

Energy diagram for a case of macroslip friction

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Figure 10

LCO dependency on the damping factor of a flutter-inducing mode: the cubic nonlinearity case

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Figure 11

LCO dependency on stiffness of the nonlinear spring

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Figure 12

Beam ODS under variation of the modal damping factor

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Figure 13

LCO dependency on the damping factor of a flutter-inducing mode: the gap nonlinearity case

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Figure 14

LCO dependency on the gap value

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Figure 15

LCO dependency on the stiffness of gap nonlinearity

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Figure 16

An FE sector model of a shrouded bladed disk

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Figure 17

LCO dependency on the damping factor of a flutter-inducing mode: a shrouded bladed disk

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Figure 18

LCO dependency on friction coefficient of the shroud contact interface

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Figure 19

LCO amplitude as a function of tangential and normal stiffness coefficients

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Figure 20

LCO frequency as a function of tangential and normal stiffness coefficients

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Figure 21

LCO amplitude as a function of normal static contact stresses and the flutter intensity

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Figure 4

Forming of LCO for different flutter intensity values

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Figure 1

Energy diagram for limit cycle oscillations

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Figure 2

An FE model of the cantilever beam

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Figure 3

Effect of FI on LCO limited by friction: (a) the whole variation range and (b) a zoomed view with small FI values

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