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Research Papers: Gas Turbines: Structures and Dynamics

A High-Accuracy Model Reduction for Analysis of Nonlinear Vibrations in Structures With Contact Interfaces

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

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

J. Eng. Gas Turbines Power 133(10), 102503 (May 06, 2011) (10 pages) doi:10.1115/1.4002810 History: Received June 01, 2010; Revised June 02, 2010; Published May 06, 2011; Online May 06, 2011

A highly accurate and computationally efficient method is proposed for reduced modeling of jointed structures in the frequency domain analysis of nonlinear steady-state forced response. The method has significant advantages comparing with the popular variety of mode synthesis methods or forced response matrix methods and can be easily implemented in the nonlinear forced response analysis using standard finite element codes. The superior qualities of the new method are demonstrated on a set of major problems of nonlinear forced response analysis of bladed disks with contact interfaces: (i) at blade roots, (ii) between interlock shrouds, and (iii) at underplatform dampers. The numerical properties of the method are thoroughly studied on a number of special test cases.

Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

A finite element model of a simple asymmetric structure: a console beam

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Figure 2

Errors for the new method with (a) ω0=0, (b) ω0=2000 Hz and (c) for the conventional modal model

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Figure 3

Finite element model and boundary conditions used in the tests

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Figure 4

Forced responses calculated with modal models and with the new methods: a case of fixed restrains on two faces

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Figure 5

Forced responses calculated with modal models and with the new methods: a case of cyclically symmetric conditions

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Figure 6

A bladed disk model used in the analysis: (a) a sector of the bladed disk, (b) contact nodes at blade root, and (c) disk contact nodes

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Figure 7

Forced responses for a case of stuck contact nodes

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Figure 8

Forced responses for a case with realistic friction

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Figure 9

An FE sector model of a shrouded bladed disk model and the shroud contact patch

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Figure 10

Effect of number of mode shapes used in pure modal modeling on forced response in the vicinity of second resonance peak: a case of full contact over all nodes

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Figure 11

Comparison of forced responses calculated with the new method: a case of stuck shrouds

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Figure 12

Forced responses calculated with the new method: a case of friction shroud contact

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Figure 13

A bladed disk with underplatform dampers: (a) a bladed disk sector and (b) an underplatform damper

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Figure 14

Comparison of forced responses calculated using the conventional modal model with 8 and 48 modes included

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Figure 15

Comparison of forced responses calculated using the new method with 4 and 48 modes included

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Figure 16

Comparison of forced responses calculated with the modal model and with the new method

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